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2018-15-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115, -132, and -133 airplanes; and Model A320- 214, -216, -232, -233, -251N, and -271N airplanes. This AD was prompted by reports of safety pins that had been installed on the inflation reservoirs of escape slides/slide rafts during production, but had not been removed. This AD requires inspecting each passenger escape slide/ slide raft to determine whether the safety pin is installed on the slide inflation reservoir, and removing any installed safety pin. We are issuing this AD to address the unsafe condition on these products.
2018-14-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of early cracking on certain holes of the crossbeam splicing at certain fuselage frames. This AD requires repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, provides an optional terminating action to the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
89-15-08: 89-15-08 BOEING: Amendment 39-6269. \n\tApplicability: All Model 737 series airplanes through line number 1581, equipped with a second observer's seat, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure structural integrity of the second observer's seat, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, install a placard above the second observer's seat, stating: "NO OCCUPANCY." This placard may be removed once the terminating action of paragraph B., below, has been accomplished. \n\n\tB.\tWithin 6 months after the effective date of this AD, inspect the second observer's seat installation for missing fasteners, in accordance with Boeing Service Letter 737-SL-25-41, dated October 14, 1988, or Boeing Service Letter 737-SL-25-41-A, dated April 20, 1989. If fasteners are found to be missing, repair prior to further flight, in accordance with the service letter. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \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\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Transport Airplane Directorate, 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 (39-6269, AD 89-15-08) becomes effective on August 24, 1989.
47-10-27: 47-10-27 LOCKHEED: (Was Mandatory Note 30 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2078. Compliance required prior to July 1, 1947. Install new type fuel tank vent outlets and add extension to fuel dump chutes. (LAC Service Bulletin 49/SB-201 covers this same subject.)
65-14-01: 65-14-01 BEECH: Amdt. 39-96 Part 39 Federal Register June 26, 1965. Applies to Models H35, J35, K35, and 35-33 Series Aircraft Equipped with Ellingsworth Products Co., Inc. Alternator Kit Number 195860 Installed Under STC SA1-377. Compliance required within the next 25 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. To prevent further failures of the alternator support bracket, accomplish the following: (a) Remove alternator supporting brackets, P/N's 195814, 195820, 195836, 195838, 195840 and 626131, thoroughly clean and inspect for elongated bolt holes. (b) Inspect brackets not having elongated bolt holes, for cracks using dye penetrant or magnetic particle method or FAA-approved equivalent. (c) Replace brackets having elongated bolt holes or cracks with unused parts of the same part number or FAA-approved equivalent before further flight. (d) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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. This directive effective June 26, 1965.
2018-12-08: We are superseding Airworthiness Directive (AD) 2017-07-07, which applied to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. AD 2017-07-07 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This AD retains the requirements of AD 2017-07-07 and expands the applicability. This AD was prompted by a report of cracking at fastener holes located at frame (FR) 40 on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products.
2018-13-08: We are superseding Airworthiness Directive (AD) 2016-01-11, which applied to certain Airbus Model A320-211, -212, and -231 airplanes. AD 2016-01-11 required repetitive inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame (FR) 36, repetitive inspections for cracking of the fastener holes of the front spar vertical stringers on FR 36, and repair if necessary. This AD adds new thresholds and intervals for the repetitive inspections; requires, for certain airplanes, a potential terminating action modification of the center wing box area; and expands the applicability. This AD was prompted by a report that, during a center fuselage certification full-scale fatigue test, cracks were found on the front spar vertical stringer at a certain frame. This AD was also prompted by a determination that, during further investigations of the frame as part of the widespread fatigue damage (WFD) campaign, certain inspection compliancetimes have to be revised and new inspections and a new potential terminating action modification have to be introduced. We are issuing this AD to address the unsafe condition on these products.
84-23-01: 84-23-01 LOCKHEED: Amendment 39-4955. Applies to Lockheed Models 1329-23A, -23D, - 23E, and -25 series airplanes, serial numbers 5001 through 5162 and 5201 through 5240, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect cracks which could lead to failure of the empennage and loss of the airplane, accomplish the following: A. Within the next 25 hours flying time or within 20 days after the effective date of this airworthiness directive (AD), inspect for cracks, proper hardware, proper installation of hardware, and loose fasteners in the JE24-1 empennage pivot fitting at the point where the fitting attaches to the flange of the JE22-1 rear beam of the vertical stabilizer in accordance with Lockheed Alert Service Bulletins A329II-55-3 and A329-299, dated October 19, 1984. If loose fasteners or cracks are found, before further flight, repair or replace with new or serviceable parts, as necessary, in accordance with a method acceptable to or approved by the FAA. B. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. This amendment becomes effective November 26, 1984.
69-07-01: 69-07-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-741. Applies to Model BAC 1-11, 200, and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To prevent interference between the flap rear pick up fitting and the flap link assembly, accomplish the following: (a) For BAC 1-11, 200, and 400 Series Airplanes with flap links P/N AB09A3697 installed, accomplish the following: (1) Within the next 160 hours' time in service after the effective date of this AD, inspect in accordance with paragraph (3) of this section to determine if a minimum clearance of 0.075 inches is provided between the flap rear pick up fitting and the flap link assembly. (2) If the inspection reveals a clearance of less than 0.075 inches, before further flight (except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be performed), incorporate BAC Modification PM 2868, as specifiedin paragraph (3) of this section. (3) Perform the inspection and modification required in paragraphs (1) and (2) of this section, in accordance with British Aircraft Corporation BAC 1-11, Alert Service Bulletin No. 27-A-PM 2245, Issue 6, dated September 16, 1968, or later ARB-approved issue, or an FAA approved equivalent. (b) For BAC 1-11, 200, and 400 Series Airplanes with flap links P/N AB09A3657 or P/N AB09A3697 installed, accomplish the following: (1) Within the next 1000 hours' time in service after the effective date of this AD, inspect in accordance with paragraph (3) of this section, the outer link positions at No. 2 and No. 3 flaps, left and right sides, for interference between the flap link and flap rear pick up fitting fork. (2) If the inspection reveals an interference, before further flight (except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be performed), incorporate BAC Modification PM 3691, as specified in paragraph (3) of this section. (3) Perform the inspection and modification required in paragraphs (1) and (2) of this section in accordance with British Aircraft Corporation BAC 1-11, Alert Service Bulletin No. 27-A-PM 2245, Issue 6, dated September 16, 1968, or later ARB-approved issue or an FAA-approved equivalent. This amendment effective March 27, 1969.
65-11-01: 65-11-01 BEECH: Amdt. 39-67 Part 39 Federal Register May 20, 1965. Applies to Model 23 Aircraft Serial Numbers M-1 through M-334 except M-62. Compliance required within 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent water from entering the static lines through the fuselage static air ports and causing a system malfunction, accomplish the following or an FAA-approved equivalent: (a) Remove the tee fitting from the static line connection just aft of the rear cabin bulkhead. (b) Connect a 52-inch length of 0.25-inch O.D. by 0.040-inch wall polyethylene tubing to the static line running under the floorboard with a 262-P-1/4 union. (c) Place the pack nut and plastic ferrule not used with the union on the other end of the tubing and connect the tee fitting. (d) Remove the clips which originally secured the static lines to the cabin bulkhead and use one to attach the static line to the top of the bulkhead just aft of the cabin bulkhead Station 239.00. (e) Shorten the tubing from each static port to provide gentle curves and to prevent any low places in the line that could trap water between the static ports and the tee. Reconnect the two shortened static port lines to the tee fitting using either the original plastic ferrules and pack nuts or new like parts. (Beech Service Bulletin No. 7 covers this same subject.) This directive effective June 19, 1965.