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2018-09-13: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports indicating additional cracking in the inspar upper skin at wing buttock line (WBL) 157 and in the skin at two holes common to the rear spar in the same area, and rear spar web cracks were also noted on both wings. Subsequent inspections revealed that the right rear spar upper chord was almost completely severed and the left rear spar upper chord was completely severed. Additional reports identified cracking in the main landing gear (MLG) beam forward support fitting. This AD requires the installation of standard-size fasteners for a certain configuration and inspections for any crack in certain locations of the rear spar. We are issuing this AD to address the unsafe condition on these products.
87-02-03: 87-02-03 THE DE HAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5514. Applies to all Model DHC-7 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude a fuel fire in the wing landing light bay, accomplish the following: A. Within the next 50 hours time-in-service after the effective date of this AD, remove the canoe fairings of the left and right No. 4 flap track from the wing lower surface and conduct a visual inspection of the external wing skin exposed, in accordance with Paragraph 1 of the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin 7- 28-18, dated May 16, 1986. If evidence of a fuel leakage is found, prior to further flight perform an internal inspection, repair, and pressure test of the fuel tank in accordance with Paragraph 2 of the Accomplishment Instructions of that service bulletin. B. Within 200 hourstime-in-service after the effective date of this AD, install Modification 7/2518 in accordance with Paragraph 3 of the Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin 7-28-18, dated May 16, 1986. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. 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 inspections and modifications required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, a Division of Boeing of Canada, Ltd., Garrett 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, Room 202, Valley Stream, New York. This amendment becomes effective January 30, 1987.
58-06-01: 58-06-01 CONVAIR: Applies to All Model 240 Series Aircraft. Compliance required not later than May 15, 1958, and at each 300 hours of operation or next regular inspection nearest thereto, on all aircraft equipped with Bendix Main Landing Gear Assemblies Nos. 155150-1, 155370-1, 159695-6 and 159589-90, with 15,000 hours or more of service time. A considerable number of reports have been received pertaining to cracking and of failures of the main landing gear axle at the 2.9998-2.9990-inch diameter adjacent to the brake flange. A number of cases resulted in complete failure of the axle and subsequent loss of main landing gear wheel. As a result of these reported failures, the subject parts must be inspected for cracks in the area described above by means of a dye penetrant or equivalent inspection procedure. Parts in which cracks are found must be considered unairworthy and be replaced or satisfactorily reworked. The repetitive inspections specified herein maybe discontinued when parts on the aircraft have been reworked in accordance with Bendix Projects Division, Aircraft Service Department Service Bulletin No. L. G. 595, Convair Newsletter No. 58-1, dated January 1958, or an FAA Western Region Aircraft Engineering Division approved equivalent. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western 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. (Bendix Projects Division, Aircraft Service Department Service Bulletin No. L. G. 595 and Convair Newsletter No. 58-1, dated January 1958, cover this same subject.) Revised September 16, 1964.
64-04-03: 64-04-03 CHAMPION: Amdt. 683 Part 507 Federal Register February 8, 1964. Applies to All Models 7GCB, 7GCBA, 7KC and All Models 7GC, 7GCA and 7HC Series Aircraft Using the 4-1099 Airscoop Box with Elliptical Fram Air Filter. Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished. As a result of several cases of engine power loss due to the carburetor alternate air door being sucked into the engine, make the spring loaded alternate air door inoperative by one of the following: (a) Locking the door in the closed position by installing a 0.040 x 1/2 x 4 1/2 5052- H34 aluminum strap or equivalent across the door and attach with two AN 515-8-6 screws and AN 365-832 nuts; or (b) Removing the entire door assembly and covering the opening with a 0.040 x 4 x 4 5052-H34 aluminum patch or equivalent. Attach the patch with eight AN 470AD3-4 rivets evenly spaced. (Champion Service Letter No. 59 covers the same subject.) This directive effective March 9, 1964.
64-04-04: 64-04-04 MACCHI: Amdt. 682 Part 507 Federal Register February 8, 1964. Applies to Aircraft Model AL.60 Serial Numbers 6/6148, 7/6149, 8/6150, 9/6154, 10/6155, 11/6156, 13/6158, 14/6159, and Model AL.60B Aircraft Serial Numbers 5/6147, 16/6161, 17/6162, 18/6163, 19/6164, 20/6165, 21/6166, 24/6169, 25/6170, 31/6211, 32/6212, 33/6213, 34/6214, 39/6219, 40/6220, 41/6221, 50/6230. Compliance required as indicated. Fuel selector valves in service have been found with defective internal "O" rings and a spring of insufficient strength. This has resulted in internal leaks through the fuel selector valve when in the closed position. (a) In order to determine whether an internal leak exists in the fuel selector valve make the following inspection within the next 10 hours' time in service after the effective date of this AD. (1) Operate the engine at maximum r.p.m. on ground. (2) Set the fuel selector valve to the off position. (3) If the engine does not stopwithin 15 seconds the fuel selector valve is defective and must be replaced, before further flight, with a modified fuel selector valve designated as 67106-1. (Macchi Service Bulletin No. 7 dated October 1, 1963, covers the same subject.) This directive effective March 9, 1964.
2018-10-05: We are superseding Airworthiness Directive (AD) 2016-23-01, which applied to all Airbus Model A310 series airplanes. AD 2016-23-01 required repetitive detailed inspections for cracking around the fastener holes in certain areas of the wing top skin panels, supplemental repetitive ultrasonic inspections for cracking around the fastener holes in certain other areas of the wing top skin panels, and repair if necessary. This AD adds an inspection and modification of the fastener holes of the wing top skin panels at a certain area. This AD also includes terminating action for certain inspections. This AD was prompted by an evaluation by the design approval holder (DAH) which indicates that the wing top skin panel fastener holes at a certain area are also subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products.
2018-09-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes and Model A319 series airplanes; all Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and all Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the holes of the upper cleat to upper stringer attachments at certain areas of the left- and right-hand wings are subject to widespread fatigue damage (WFD). This AD requires modifying the holes of the upper cleat to upper stringer attachments at certain areas of the left- and right-hand wings. We are issuing this AD to address the unsafe condition on these products.
64-02-03: 64-02-03 CALLAIR: Amdt. 672 Part 507 Federal Register January 17, 1964. Applies to All Models A-5 and A-6 Aircraft. Compliance required as indicated. As a result of several failures of the front attaching tube of the horizontal stabilizer, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD check for cracks as follows: (1) Remove the horizontal stabilizers from the airplane and thoroughly clean the leading edge tube of the horizontal stabilizer by removing all paint, rust, and foreign materials. Check for cracks in the area where the tube attaches to the fuselage carry through member and also around the horizontal tail fixed handle area where the tube has been bent back to provide sweepback. (2) Inspect for cracks using the magnetic particle inspection process. (b) If cracks are found, either install a new stabilizer or make an FAA approved repair. Thereafter reinspect the stabilizer at intervals not to exceed 100 hours' time in service. (c) If no cracks are found, reinstall stabilizers and reinspect at intervals not to exceed 100 hours' time in service. (d) CallAir Service Kit No. 10 provides a suitable reinforcement of the empennage by the installation of additional brace wires to the forward portion of the tail surfaces. No further periodic inspections are required if CallAir Service Kit No. 10 is installed with a new or repaired horizontal stabilizer. (CallAir Service Bulletin No. 10 covers this same subject.) This directive effective January 17, 1964.
2005-13-28: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes. This AD requires a one-time inspection of the clevis end of the vertical tie rods that support the center stowage bins to measure the exposed thread, installation of placards that advise of weight limits for certain electrical racks, a one-time inspection and records check to determine the amount of weight currently installed in those electrical racks, corrective actions, and replacement of the vertical tie rods for the center stowage bins or electrical racks with new improved tie rods, as applicable. The actions specified by this AD are intended to prevent failure of the vertical tie rods supporting certain electrical racks and the center stowage bins, which could cause the center stowage bins or electrical racks to fall onto passenger seats below during an emergency landing, impeding an emergency evacuation or injuring passengers. This action is intended to address the identified unsafe condition.
2018-10-04: We are superseding Airworthiness Directive (AD) 2018-03-15 for Pacific Aerospace Limited Model 750XL 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 reports of finding abrasion damage behind the instrument panel caused by ventilation hose chafing. We are issuing this AD to require actions to address the unsafe condition on these products.