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2000-25-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, and -200C series airplanes. This action requires repetitive inspections of the aft end of each inboard flap track of the wing outboard flap, and corrective actions, if necessary. This action is necessary to detect and correct damage of the aft end of each flap track, which could result in loss of the outboard trailing edge flap and consequent loss of controllability of the airplane.
88-04-10: 88-04-10 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5855. Applies to Model DHC-7 series airplanes, equipped with Modification No. 7/2414, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude the possibility of heat shield separation resulting from the failure of aluminum alloy washers, accomplish the following: A. Within 60 days or 500 flight hours, whichever occurs first after the effective date of this AD, replace aluminum alloy washers with stainless steel washers, in accordance with the Accomplishment Instructions of de Havilland DHC-7 Service Bulletin No. 7-57-29, dated August 1, 1986. B. An 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, New York Aircraft Certification Office, FAA, New England Region. 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. All persons affected by this directive who have not already received the appropriate service documents 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. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment becomes effective April 5, 1988.
2000-25-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Pratt & Whitney (PW) PW4000 turbofan engines with the current design low pressure turbine (LPT) 4th stage air seal installed. This action requires, based on engine model, replacement of the current design seal with a new design seal, or with a modified seal. This amendment is prompted by reports of cracks in LPT 4th stage air seals. The actions specified by this AD are intended to reduce stresses that could lead to LPT 4th stage air seal cracking, resulting in seal fracture, uncontained engine failure, and damage to the airplane.
2016-06-01: We are superseding an airworthiness directive (AD) 2007-06-06 for B-N Group Ltd. Models BN-2, BN-2A, BN-2A-2, BN-2A-3, BN-2A-6, BN- 2A-8, BN-2A-9, BN-2A-20, BN-2A-21, BN-2A-26, BN-2A-27, BN-2B-20, BN-2B- 21, BN-2B-26, BN-2B-27, BN2A MK. III, BN2A MK. III-2, BN2A MK. III-3 BN2A, BN2B, and BN2A MKIII (all models on TCDS A17EU and A29EU) airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks in the inner shell of certain pitot/static pressure heads. We are issuing this AD to require actions to address the unsafe condition on these products.
52-17-02: 52-17-02 CURTISS-WRIGHT: Applies to all Model C-46 Series aircraft. Compliance required as noted. As a result of a number of failures the following precautionary measures must be taken: 1. The original compliance date set was not later than December 1, 1952, and at each No. 3 inspection thereafter, however, in order to convert the inspection interval to time in service, the following inspection shall be accomplished within 400 hours' time in service after the effective date of this amendment. Subsequent compliance required at each 400 hours' time in service after initial compliance. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. Inspect the tail wheel shimmy damper support, P/N 20-360-3108-4, for cracks or damage which might lead to subsequent failure. Particular attention should be paid to the radius formed by the intersection of the vertical and lower horizontal surface on the forward side of the part. A general inspection of the shimmy damper assembly should be made and it should be determined that it is properly adjusted. All cracked or damaged parts must be replaced. The following method of adjustment of the shimmy damper as outlined in Air Force Technical Order AN 01-25LA-2, section IV, paragraph 8 (f) is quoted below for your convenience: (a) Position the shimmy damper on the mounting bracket and attach the two 3/8-inch bolts, nuts, and washers, using a 9/16-inch open-end wrench in conjunction with a 9/16- inch socket and a ratchet. (b) Before installing the link assembly to the shimmy damper arm, the arm must be positioned to allow for maximum travel of the unit in actual operation. This is accomplished by slowly actuating the arm toward the rear of the airplane until the movement stops. From this point reverse the action until the arm has made an arc of 67 degrees. It is now in a neutral position and will assure correct operation when completely installed. (c) With the arm in neutral and making sure not to move it from this position, attach the link assembly to it with the 5/16-inch bolt, nut, washer and cotter pin using a 1/2-inch open-end wrench, a 1/2-inch socket, and a ratchet. (d) Make sure that the tail wheel is locked in position. The pin on the centering disc will then be properly set for attaching the eyebolt of the link assembly. If the eyebolt hole does not match with the pin on the centering disc when the tail wheel is locked and the actuating arm is in neutral, adjustment must be made by loosening the locknut on the eyebolt and turning the eyebolt until the proper length is obtained. Be sure to tighten the locknut again.(e) Secure the link assembly to the centering disc by installing the 1 1/8-inch castellated nut and washer drawing up the nut with a crescent wrench. Insert a cotter pin on this nut. 2. Compliance required as noted. Tail wheel locks for the subject model airplane have been manufactured which do not comply with the material specifications and in some cases physical dimensions of the approved drawings. The approved tail wheel lock P/N 20-360-1033, is a forged steel part of 8740 or N-S- 16 material heat treated to 150,000 pounds per square inch, with a Rockwell harness of C-33 to C-38; however, a cast steel lock complying with the physical dimensions, heat treat and hardness of the approved drawing will also be considered acceptable. The original compliance date for the following inspection was March 1, 1953; however, in view of a recent accident involving the installation of an unapproved tail wheel lock, it must be ascertained prior to February 15, 1956, that all tailwheel locks meet the stated specifications of an acceptable part. Any tail wheel locks which do not comply with the approved drawing, No. 20-360-1033, in regard to material, heat treat or physical dimensions as mentioned above, must be replaced with an approved part. It should be noted that some unsatisfactory parts in circulation bear the correct part number, therefore this fact cannot be considered a satisfactory means of determining that an approved part is installed in the airplane. Revised October 23, 1961. Revised November 23, 1961.
93-10-08: 93-10-08 DE HAVILLAND: Amendment 39-8588. Docket No. 91-CE-49-AD. Supersedes AD 73-19-06, Amendments 39-1800 and 39-1710. Applicability: Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes (serial numbers 1 through 420), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the overhead control console, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished within the last 175 hours TIS (compliance with AD 73-19-06), visually inspect the overhead console control quadrants for cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland Service Bulletin (SB) 6/298, Revision D, dated December 20, 1991. (1) If cracks are found that meet or exceed the requirements specified in paragraph 3.1 of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/298, Revision D, dated December 20, 1991, prior to further flight, replace the overhead control console quadrants, part number (P/N) C6-CE-1010, with P/N C6CE1421-27 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/298. (2) If cracks are found that meet or exceed the requirements specified in paragraph 3.2 of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/298, Revision D, dated December 20, 1991, within the next 200 hours TIS, replace the overhead control console quadrants, P/N C6-CE-1010, with P/N C6CE1421-27 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/298. (3) If cracks are found that are less than that specified in paragraph 3.2 of the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/298, Revision D, dated December 20, 1991, reinspect at intervals not to exceed 100 hours TIS until the modification specified in paragraph (b) of this AD is accomplished. (4) If no cracks are found, reinspect at intervals not to exceed 200 hours TIS until the modification specified in paragraph (b) of this AD is accomplished. (b) Within the next 2,400 hours TIS after the effective date of this AD, unless already accomplished as specified in paragraph (a)(1) or (a)(2) of this AD, replace the overhead control console quadrants, P/N C6-CE-1010, with P/N C6CE1421-27 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of de Havilland SB No. 6/298, Revision D, dated December 20, 1991. (c) The installation of new overhead control console quadrants (Modification No. 6/1467) as specified in paragraphs (a)(1), (a)(2), and (b) of this AD is considered terminating action for the repetitive inspection requirement of this AD. (d) 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. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, New York Aircraft Certification Office, 181 Franklin Avenue, Room 202, Valley Stream, New York 11581. The request shall be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, New York Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York Aircraft Certification Office. (f) The inspections and modification required by this AD shall be done in accordance with de Havilland Service Bulletin (SB) 6/298, Revision D, dated December 20, 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 de Havilland, Inc., 123 Garratt Boulevard, Downsview, Ontario, Canada, M3K 1Y5. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (g) This amendment (39-8588) supersedes AD 73-19-06, Amendments 39-1800 and 39-1710. (h) This amendment becomes effective on July 16, 1993.
2000-24-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Rolls-Royce plc RB211 Trent 800 series turbofan engines, that currently requires initial and repetitive ultrasonic inspections of fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment requires the reduction of the initial cyclic compliance threshold and repetitive inspection intervals. This amendment also allows inspections to be accomplished within 100 cycles-in-service if the initial or repetitive thresholds are exceeded on the effective date of this AD. This amendment is prompted by an improved understanding of the crack propagation mechanism and the latest service operational data. The actions specified by this AD are intended to detect and prevent fan blade failure, which could result in multiple fan blade releases, uncontained engine failure, and possible damage to the airplane.
2016-05-09: We are adopting a new airworthiness directive (AD) for certain MDHI Model 369A (Army OH-6A), 369H, 369HE, 369HM, 369HS, 369D, 369E, 369F, 369FF, and 500N helicopters. This AD requires inspecting the auxiliary fuel pump (fuel pump) wire routing in the left-hand fuel cell and corrective action, if necessary. This AD also requires installing a warning decal on the left-hand fuel cell access cover. This AD was prompted by accidents resulting from incorrectly positioned fuel pump wiring within the fuel tank interfering with the operation of the fuel quantity sensor float, which caused an erroneous fuel quantity indication in the cockpit. The actions are intended to detect and correct routing of the fuel pump wiring to prevent interference with the fuel quantity sensor float, an erroneous fuel quantity indication in the cockpit, and subsequent fuel exhaustion and emergency landing.
2009-03-03: We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes listed above. This AD requires installing a dam assembly for the container of the fuel boost pump of the center tank located in the right main tank, and doing the related investigative actions, and corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the center tank fuel boost pump from operating in a fuel vapor zone and becoming a potential ignition source in the right main tank, potentially resulting in a fuel tank explosion and consequent loss of the airplane.
73-20-07 R2: 73-20-07 R2 BEECH: Amendment 39-1728 as amended by Amendment 39-3732 is further amended by Amendment 39-4461. Applies to Models A23-19, 19A, M19A, B-19 (Serial Numbers MB-1 through MB-708); Models 23, A23, A23A, B23, C23 (Serial Numbers M-1 through M-1576); Models A23-24, A24 (Serial Numbers MA-1 through MA-368); and Models A24R, B24R (Serial Numbers MC-2 through MC-282) certified in all categories. Compliance: Required as indicated. To detect cracks or other structural damage to the forward wing attach point brackets (P/N 169-400013-3 and -5(LH) and 169-400013-4 and -6 (RH)), within the next 25 hours' time in service after the effective date of this AD unless previously accomplished on airplanes having more than 100 hours' time in service and thereafter at each normal annual, progressive or 100 hour inspection interval as required by FAR 91.169, accomplish the following: (a) Remove the seats and sidepanels and visually inspect the forward wing attach brackets, P/N169-400013-3 and -5 (LH) and 169-400013-4 and -6 (RH), to determine if cracks or other structural damage exists in the area around the attach bolt hole. This inspection is to be performed in accordance with Beech Service Instructions 0042-031, Rev. II. (b) If as a result of any inspection required herein cracks or other structural damage is discovered, prior to further flight repair the forward wing attach brackets in accordance with Beechcraft Service Instructions 0042-031, or later FAA-approved revisions, or any other repair approved by the Chief, Wichita Aircraft Certification Office, FAA, Wichita, Kansas. To accomplish the repair required herein the aircraft may be flown in accordance with FAR 21.197 to a base where the repair may be performed. (c) The inspection intervals required in this AD may be adjusted 15 plus or minus hours where required to fit users maintenance cycles if authorized by an FAA Flight Standards Inspector. (d) When airplanes have been modified by installing all of the new wing attach structural parts listed under materials in Beechcraft Service Instructions No. 0042-031, Rev. II, further compliance with this AD is not required. (e) Any equivalent method of compliance with this AD must be approved by the Chief, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. Amendment 39-1728 became effective October 5, 1973. Amendment 39-3732 became effective March 21, 1980. This Amendment 39-4461 became effective on September 3, 1982.