Results
2017-12-08: We are superseding Airworthiness Directive (AD) 2011-24-06 for all BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and - 300A airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes. AD 2011-24-06 required revising the maintenance program to incorporate life limits for certain items, adding new and more restrictive inspections to detect fatigue cracking in certain structures, and adding fuel system critical design configuration control limitations (CDCCLs) to prevent ignition sources in the fuel tanks. AD 2011-24-06 also required modifying the main fittings of the main landing gear (MLG) and revising the maintenance program to incorporate new life limits on MLG up-locks and door up-locks and other MLG components. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. This AD was prompted by a determination that new or revised structural inspection requirements are necessary. We are issuing this AD to address the unsafe condition on these products.
2024-13-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report of heat damage on multiple engine inlets around the engine anti-ice (EAI) duct within the inlet aft compartment. This AD requires doing a records check and updating the operator's existing minimum equipment list (MEL), inspecting the left and right engine inlet cowl assembly for signs of heat damage around the EAI duct, installing or replacing the EAI duct seals, repairing any damage, and replacing the engine inlet if necessary. This AD also prohibits the installation of engine inlets under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
91-13-10 R1: 91-13-10 R1 BOEING: Amendment 39-8158. Docket No. 91-NM-241-AD. Revises AD 91-13-10, Amendment 39- 7041. \n\n\tApplicability: Model 747 series airplanes equipped with Pratt and Whitney PW4000 engines; and Model 767 series airplanes equipped with Pratt and Whitney PW4000, General Electric CF6-80C2-B2F, or General Electric CF6- 80C2-B6F series engines; certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\tTo prevent overspeed or uncommanded shutdown of an engine, accomplish the following:\n\n\t(a)\tFor Model 747 series airplanes equipped with Pratt and Whitney PW4000 engines, and Model 767 series airplanes equipped with Pratt and Whitney PW4000 or General Electric CF6-80C2-B6F engines: Within 3 days after May 22, 1989 (the effective date of Amendment 39-6210), add the following to the Limitations Section of the FAA- approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t"Prior to each departure, with all engines running, refer to the EICAS status page and determine the dispatch capability of the aircraft." \n\n\t(b)\tWithin the next 24 months after August 12, 1991 (the effective date of this Amendment 39-7041), replace the EICAS computers in accordance with the appropriate service bulletin listed below. After replacement of the EICAS computers in accordance with the specified service bulletins, the AFM limitation required by paragraph (a) of this AD may be removed. \n\n\t\t(1)\tFor Model 747 series airplanes listed in Boeing Service Bulletin 747-31-2151, dated March 29, 1990. \n\n\t\t(2)\tFor Model 767 series airplanes equipped with Pratt and Whitney PW4000 engines listed in Boeing Service Bulletin 767-31-0033, Revision 1, dated September 27, 1990. \n\n\t\t(3)\tFor Model 767 series airplanes equipped with General Electric CF6-80C2-B6F engines listed in Boeing Service Bulletin 767-31-0038, dated April 12, 1990. \n\n\t(c)\tFor Model 767 series airplanes equipped with General Electric CF6-80C2-B2F engines: \n\n\t\t(1)\tWithin the next 3 days after the effective date of this AD, add the following to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t"Prior to each departure, with all engines running, refer to the EICAS status page and determine the dispatch capability of the aircraft." \n\n\t\t(2)\tWithin the next 24 months after the effective date of this AD, replace the EICAS computers in accordance with Boeing Service Bulletin 767-31-0038, dated April 12, 1990. After incorporation of the EICAS computers, the AFM limitation required by paragraph (c)(1) may be removed. \n\n\t(d)\tFor airplanes not subject to paragraph (b) or (c) of this AD, within the next 30 days after the effective date of this AD, remove the AFM limitation required by paragraph (a) of this AD. \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance time, which provides anacceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(f)\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\t(g)\tThe replacement requirements shall be done in accordance with the following Boeing Service Bulletins, which incorporate the following list of affected pages: \n\nService Bulletin\tRevision Level\t\tDate\t\t\tPages \n\n747-31-2151\nOriginal\t\nMarch 29, 1990\n1 - 10 \n767-31-0033\n1\nOriginal\t\nSeptember 27, 1990 May 31, 1990\n1, 2, 4, 5 \n3, 6, 7, 8, \n9, 10 \n767-31-0038\nOriginal\t\nApril 12, 1990\n1 - 8 \n\n\n\n\n\t\nThis incorporation by reference was approved by the Director of the Federal Register inaccordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.\n\n\t(h)\tAirworthiness Directive 91-13-10 superseded AD 89-10-06, Amendment 39-6210. \n\t(i)\tThis Airworthiness Directive 91-13-10 R1 revises AD 91-13-10, Amendment 39-7041.\n \t(j)\tThis amendment (39-8158, AD 91-13-10 R1) becomes effective on February 26, 1992.
2024-14-03: The FAA is adopting a new airworthiness directive (AD) for various airplanes modified with a certain configuration of the Garmin GFC 500 Autopilot System installed per Supplemental Type Certificate (STC) No. SA01866WI. This AD was prompted by a report of an un- commanded automatic pitch trim runaway when the autopilot was first engaged. This AD requires updating the applicable Garmin GFC 500 Autopilot System software for your airplane and prohibits installing earlier versions of that software. The FAA is issuing this AD to address the unsafe condition on these products.
2017-12-04: We are superseding airworthiness directive (AD) 2016-20-04 for Airbus Helicopters Model SA341G and SA342J helicopters. AD 2016-20-04 prohibited autorotation training flights until the landing gear rear crosstube (crosstube) was inspected. This new AD adds additional part- numbered crosstubes to the applicability and revises the hardness criteria for the inspection. This AD is prompted by a determination that an additional part-numbered crosstube may have the same unsafe condition. The actions of this AD are intended to detect and prevent an unsafe condition on these helicopters.
2017-11-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin lap splices are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections to detect any crack in the fuselage skin at the skin lap splices, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
91-05-09: 91-05-09 PILATUS BRITTEN-NORMAN (PBN): Amendment 39-6892; Docket No. 90-CE-33-AD. Applicability: Model BN-2T Turbine Islander airplanes (all serial numbers), certificated in any category, that do not have PBN Modification Number NB/M/1429 incorporated. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent the loss of engine power on both engines simultaneously, accomplish the following: (a) Modify the airplane engine ignition system as described in PBN Service Bulletin BN-2/SB 193, dated April 11, 1990. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (d) All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge Airport, Isle of Wight, PO36 5PR, England; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6892, AD 91-05-09) becomes effective on March 25, 1991.
77-22-05: 77-22-05 BELLANCA (CHAMPION): Amendment 39-3069. Applies to models 7ECA S/Nos. 1 thru 722, 725, 723-70 thru 1238-78 7GC S/Nos. All 7GCA S/Nos. All 7GCAA S/Nos. 1 thru 198, 200 thru 204, 276, 205-70 thru 355- 78 7GCB S/Nos. All 7GCBC S/Nos. 1 thru 201, 205, 207, 202-70 thru 1024-78 7HC S/Nos. All 7KCAB S/Nos. 1 thru 208, 210 thru 226, 270, 271, 209-70 thru 617-77 Certificated in all categories. Compliance is required as indicated unless already accomplished. Part I Airspeed Restriction/Front Strut Replacement a. Effective immediately, unless already accomplished, attach the following operating limitation placard near the airspeed indicator in full view of the pilot: "DO NOT EXCEED 153 MPH CAS MAXIMUM OPERATING SPEED" The letters on this placard must be at least 1/8 inch in height and on suitable material which can be expected to remain affixed in position and resist deterioration. This placard may be installed by the pilot.b. Within three (3) months after the effective date of this airworthiness directive, accomplish either: 1. Remove red radial marking on airspeed indicator at 162 MPH (141 KTS). Remark indicator with red radial line at 153 MPH (133 KTS). Change Operations Limitations Card as follows: Replace Airspeed Limitations "GLIDE or DIVE-----162 MPH CAS" with "MAXIMUM OPERATING SPEED----153 MPH CAS". Bellanca Service Kit 256 may be used to accomplish this. (Bellanca Service Letter C-127 pertains to this subject.) After marking indicator, the placard required per paragraph (a) above may be removed, or 2. Remove wing front lift struts Bellanca P/N 5-144 and install replacement wing front lift struts Bellanca P/N 5-392 (Bellanca Service Letter C-127 and Service Kit 257 pertain to this subject). After the struts are replaced, the placard per paragraph (a) above may be removed and the airspeed markings and Operations Limitations Card per paragraph (b.1) above may be returned to theiroriginal 162 MPH CAS markings. NOTE: The Bellanca P/N 5-392 strut may be identified by a square tube fitting at the wing end. Part II Acrobatic Maneuvers Placard/Accelerometer Markings/Operating Limitations Card Change. Applies to All Bellanca (Champion) Acrobatic Models As Indicated. (Bellanca Service Letter C-128 pertains to this subject.) a. Effective immediately, flight operations shall be conducted in accordance with the limitations specified below. b. Within three (3) months after the effective date of this airworthiness directive unless already accomplished, replace the acrobatic maneuvers placard and remark the accelerometer if applicable as indicated below. 1. For Model 7ECA - S/Nos. 1 thru 722, 725, 723-70 thru 1238-78 7GCAA - S/Nos. 1 thru 198, 200 thru 204, 276, 205-70 thru 355-78 Install Bellanca placard (Bellanca Service Kit 258) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below. LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION DO NOT EXCEED +5.0 OR -2.0 G LOAD FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITIONS. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. CAUTION: NEGATIVE G FLIGHT WILL CAUSE LOSS OF OIL AND OIL PRESSURE. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 2. For Model 7GCBC - S/NOS. 1 THRU 201, 205, 207, 202-70 thru 1024- 78 7GCB - Aircraft approved in acrobatic category only Install Bellanca placard (Bellanca Service Kit 259) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below. LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION DO NOT EXCEED +5.0 OR -2.0 G LOAD FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. CAUTION: NEGATIVE G FLIGHT WILL CAUSE LOSS OF OIL AND OIL PRESSURE. USE OF FLAPS DURING ACROBATICS PROHIBITED. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 3. For Model 7KCAB - S/Nos. 1 thru 208, 210 thru 226, 270, 271, 209-70 thru 404-73, 405-74 thru 458-74, 460-74 thru 508-75 Install Bellanca placard (Bellanca Service Kit 260) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below: LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION LEVEL INVERTED FLIGHT 120 104 135 MPH (117 KTS) IAS MAX DO NOT EXCEED +5.0 or -2.0 G LOAD FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. INVERTED FLIGHT LIMITED TO 2 MIN - MONITOR OIL PRESS WHILE INVERTED TO INSURE MINIMUM OF 60 PSI. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 4. For Model 7KCAB - S/Nos. 459-74, 509-75 thru 617-77 Install Bellanca placard (Bellanca Service Kit 261) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION LEVEL INVERTED FLIGHT 120 104 135 MPH (117 KTS) IAS MAX DO NOT EXCEED +5.0 OR -2.0 G FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. 2 MIN OF INVERTED FUEL NORMALLY AVAILABLE. MOMENTARY OIL PRESSURE INTERRUPTIONS ARE NORMAL. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 5. If aircraft is equipped with accelerometer, verify that the red radial marks are installed at +5.0 G and -2.0 G. If markings are incorrect, remark indicator. c. Within the next 30 days after the effective date of this airworthiness directive, unless already accomplished, attach the following placard near the airspeed indicator in full view of the pilot. The placard will be a facsimile of the following on suitable material which can be expected to remain affixed in position and resist deterioration as shown below: "DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION" This placard is available as a part of the Service Kits described in parts (1) through (4) above. d. For Model 7KCAB, within three (3) months after the effective date of this airworthiness directive, verify that the Operating Limitations Card presents the following information. If markings are incorrect, remark Operating Limitations Card. Replacement Operating Limitations Cards are available in Bellanca Service Kit 262. Maneuvering Flight Limit Load Factors Positive ------------------ 5.0 g Negative ---------------- 2.0 g DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. This amendment becomes effective November 7, 1977.
91-26-07: 91-26-07 BRITISH AEROSPACE: Amendment 39-8118. Docket No. 91-NM-245-AD. Applicability: British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes equipped with G.E.C. Plessey generator control units (GCU); as listed in British Aerospace Alert Service Bulletin 24-A97, dated November 12, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inaccurate flight instrument readings, accomplish the following: (a) Within 10 days after the effective date of this AD, replace G.E.C. Plessey GCU's having part number 700-1-22490-410 or 700-1-22490-510, with G.E.C. Plessey GCU's having part number 700-1-22490-400 or 700-1-22490-500, in accordance with British Aerospace Alert Service Bulletin 24-A97, dated November 12, 1991. (b) An alternative method 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, 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 replacement shall be done in accordance with British Aerospace Alert Service Bulletin 24-A97, dated November 12, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles InternationalAirport, Washington, DC. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective June 16, 1992.
2017-12-02: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, -1B67, - 1B67/P1, -1B67/P2, -1B70, -1B70/P1, -1B70/P2, -1B70/75/P1, -1B70/75/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76A/P2 turbofan engines. This AD was prompted by a fracture of the fuel manifold which led to an in-flight shutdown of the engine. This AD requires replacement of the outer left side signal fuel manifold with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products.