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84-03-06: 84-03-06 BOEING AND McDONNELL DOUGLAS: Amendment 39-4805. Applies to Boeing Model 747 and McDonnell Douglas Model DC-9 and DC-10 series airplanes certificated in all categories:\n\n\tA.\tWithin 180 days from the effective date of this AD, unless already accomplished, determine if any components listed by serial number in Table I, below, are installed on or in the landing gear assembly. This determination may be made by review of records or by inspection of parts to determine serial numbers. Components delivered with production airplanes or purchased from Boeing, Douglas, or Cleveland Pneumatics, as spares, are not affected by this AD. Components purchased prior to January 1, 1979, are not affected by this AD.\n\n\tB.\tIf any components listed in Table I are found, replace them with approved parts before further flight.\n\n\tC.\tFuture use of any components listed by serial number in Table I is prohibited, unless it is determined by the manufacturer or demonstrated to the FAA that thecomponent is in conformity to type design.\n\n\tD.\tUpon request of the operator, an FAA Principal Maintenance Inspector may adjust the compliance times if the request contains substantiating data to justify the change, and subject to prior approval by the Manager, Seattle Aircraft Certification Office, for the Boeing Model 747, or the Manager, Los Angeles Aircraft Certification Office, for the McDonnell Douglas Models DC-9 and DC-10.\n\n\tE.\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office for the Boeing Model 747, or the Manager, Los Angeles Aircraft Certification Office for the McDonnell Douglas Models DC-9 and DC-10.\n\n\tF.\tAircraft may be ferried to a base for maintenance in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations.\n\n\tThis amendment becomes effective March 19, 1984.\n\n\t\t\t\t\t\tAD 84-03-06\n\t\t\t\t\t\tTABLE I\n\n\n\nPART\nAIRCRAFT\nSERIAL\nAIRCRAFT\nNOMENCLATURE\nMANUFACTURERS\nNUMBERS\n\n\n PART NO.\n\n\n\n\n\nBoeing\nBrace Assembly\n65B05280\nCPT 1163 PTM\n747-100\nSide Body\n\nCPT 1257 PTM\n /200\nLanding Gear\n\n\n\nAxle\n65B05133\nCPT 2474 PTM\n\nWing & Body\n\nCPT 2714 PTM\n\nGear\n\nCPT 2828 PTM\n\n\n\nCPT 2836 PTM\n\n\n\nCPT 2838 PTM\n\n\n\nCPT 2839 PTM\n\n\n\nCPT 2886 PTM\n\n\n\nCPT 2908 PTM\n\n\n\nCPT 2959 PTM\n\n\n\nCPT 2981 PTM\n\n\n\nCPT 2982 PTM\n\n\n\nCPT 2991 PTM\n\n\n\nCPT 3048 PTM\n\n\n\nCPT 3056 PTM\n\n\n\nCPT 3063 PTM\n\n\n\nCPT 3090 PTM\n\n\n\nCPT 3091 PTM\n\n\n\nCPT 3101 PTM\n\n\n\nCPT 3149 PTM\n\n\n\nCPT 3691 PTM\n\n\n\nCPT 3733 PTM\n\n\n\n\nBoeing\nAxle\n65B19917\nCPT 3398 PTM\n747-SP\nWing & Body\n\n\n\nGear\n\n\n\n\n\n\nMcDonnell\nNose Gear Cylinder\n5920602-5\nCPT 1134 PTM\nDouglas\n\n or\nCPT 1160 PTM\nDC-9\n\n5920602-501\nCPT 1201 PTM\n\n\n\nCPT 1207 PTM\n\n\n\nCPT 1210 PTM\n\n\n\nCPT 1129 PTM\n\n\n\n\n\nNose Gear Piston\n5920603-501\nCPT 1395 PTM\n\n\n or\nCPT 1310 PTM5920603-5\nCPT 1308 PTM\n\n\n\nCPT 1417 PTM\n\n\n\nCPT 1422 PTM\n\n\n\nCPT 1440 PTM\n\n\n\nCPT 1301 PTM\n\n\n\nCPT 1306 PTM\n\n\n\nCPT 1160 PTM\n\n\n\nCPT 1161 PTM\n\n\n\nCPT 1178 PTM\n\n\n\nCPT 1208 PTM\n\n\n\nCPT 1209 PTM\n\n\n\nCPT 1246 PTM\n\n\n\n\nMcDonnell\nMain Gear Link Assy\nARG7009-501\n\nDouglas\nLower Down Lock\n or\nCPT 402 PTM\nDC-10\n\nARG7009-7\nCPT 421 PT\n\n\n\n\n\nAxle MLG\nARG7313-3\n\n\n\n or\nCPT 4361 PTM\n\n\nARG7313-1\n\n\n\n\n\n\nLink\nARG7107-5\n\n\n\n or\n\n\n\nARG7107-1\nCPT 0886 PTM\n\n\n\n\n\nBolt - Torque\nARG7323-1\nM 495 PTM\n\nLink - Upper\n\n\n\n MLG\n\n\n\n\n\n\n\nArm - Downlock\nARG7147-1\nCPT 1328 PTM\n\nMLG\n or\n\n\n\nARG7147-3\n\n\n\n\n\n\nLink Assembly\nARG7019-1\nCPT 019 PTM\n\nForward Brake\n or\nCPT 941 PTM\n\n\nARG7019-5\n\n\nLink Assembly\nARG7378-1\nCPT 672 PTM\n\nForward Brake\n or\nCPT 941 PTM\n\n MLG\nARG7378-3\n\n\n\n\n\n\n\n\n\n\nBolt - Torque\nARG7337-1\nCPT 063 PTM\n\nLink - Lower\n\nCPT 039 PTM\n\n MLG\n\nCPT 073 PTM\n\n\n\nCPT 040 PTM\n\n\n\nCPT 041 PTM
83-07-14: 83-07-14 BEECH: Amendment 39-4628. Applies to Models F90 (S/Ns LA-2 through LA-7 and LA-103 through LA-146), 200 (S/Ns BB-2 through BB-525, BB-789 through BB-792, BB- 794 through BB-828 and BB-830 through BB-852), 200C (S/Ns BL-18 through BL-36), 200CT (S/N BN-1), 200T (S/Ns BT-1 through BT-7), B200 (S/Ns BB-793, BB-829, BB-854 through BB-868, and BB-870), and B200C (S/N BL-37) airplanes certificated in any category. COMPLIANCE: Required as indicated, unless already accomplished. To prevent decompression and possible injury caused by failure of a one-ply window that may have been installed instead of the required multi-ply window, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: a) Inspect all windows and replace each one-ply window that is found with the required multi-ply window in accordance with the criteria contained in Beechcraft Service Instructions Number 1214. b) Airplanes may be flown in accordance with Federal Aviation Regulation 21.197 to a place where this AD may be accomplished, provided a maximum pressure altitude of 25,000 feet and a maximum differential cabin pressure of 4.6 pounds per square inch is not exceeded. c) An equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid- Continent Airport, Wichita, Kansas 67209, telephone (316) 269-7000. This amendment becomes effective on April 18, 1983.
2019-03-16: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.27 Mark 100, 200, 300, 400, 500, 600, and 700 airplanes. This AD was prompted by a report of a main landing gear (MLG) collapse due to a broken drag stay; an investigation revealed that the drag stay failure was due to fatigue cracks, introduced by incorrect machining of the affected drag stay tube during production. This AD requires an inspection of the drag stay unit to determine the signal indication, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
87-18-05 R1: 87-18-05 R1 BOEING: Amendment 39-5722 as revised by Amendment 39-6242. \n\n\tApplicability: Model 767 series airplanes, equipped with General Electric CF6 engines, listed in Boeing Service Bulletin 767-29-0032 dated January 15, 1987, and airplanes Serial Numbers 22322, 23431, 23432, 23494, 23623, and 23624, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent cracking of the hydraulic pressure line aluminum support brackets in the engine strut, and possible fuel line penetration, accomplish the following: \n\n\tA.\tFor airplanes listed in Boeing Service Bulletin 767-29-0032, dated January 15, 1987: Within the next 3,000 hours time-in-service after October 7, 1987 (which is the effective date of Amendment 39-5722), replace aluminum brackets with inconel brackets at three locations in each engine strut area to support the hydraulic pressure line, in accordance with that service bulletin. \n\n\tB.\tFor all other airplanes:Within the next 3,000 hours time-in-service after the effective date of this amendment, replace aluminum brackets with inconel brackets at three locations in each engine strut area to support the hydraulic pressure line in accordance with Boeing Service Bulletin 767-29-0032, Revision 1, dated June 16, 1988. \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 for the accomplishment of 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, 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 revises Amendment 39-5722, AD 87-18-05, which became effective on October 7, 1987. \n\n\tThis amendment (39-6242, AD 87-18-05 R1) becomes effective on July 24, 1989.
2005-24-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, that requires an inspection of the thrust reverser cascades for correct installation; removing and reinstalling the cascade in the correct location, if necessary; and reworking the thrust reverser cascades to add locating spigots (metal protrusions) to each cascade; as applicable. This action is necessary to prevent asymmetric reverse thrust and consequent loss of control of the airplane during reverse thrust operation. This action is intended to address the identified unsafe condition.
98-21-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that currently requires deactivation of certain floormat heaters in the cabin area. In addition, that AD provides for optional terminating action for that deactivation. This amendment removes the optional terminating action of the existing AD and adds airplanes to the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent short circuiting between the flight attendant's floormat heater and the floor panel, which could cause overheating of the floormat heater and lead to smoke or fire in the airplane cabin.
50-40-01: 50-40-01 BOEING: Applies to all Model 377 Aircraft. A. Compliance required not later than December 15, 1950, unless already accomplished, and at the periodic inspections nearest a 700-hour interval thereafter if not reinforced as indicated below. Thoroughly inspect the nose gear spindle for circumferential cracks in the area adjacent to the weld between the nose gear spindle shaft, P/N 9-13735, and the spindle bearing, P/N 6- 25978. Since these cracks are extremely fine, a close magnaflux, dye penetrant or equivalent inspection is required. (Etching process is not recommended.) If cracks are found, either of the following steps should be taken: (1) Remove the cracks with 3/8-inch diameter grinding tool such that not more than 0.08 inch of the spindle shaft and not more than 0.10 inch of the weld is removed. (Boeing Service Letter No. 94 covers this subject.) If cracks extend beyond these limits the spindle should be reinforced per item (2) below: (2) Reinforcethe nose gear spindle by machining inside of spindle and inserting a 1/2-inch wall steel tube 25-inches long, P/N 5-39516-3. (Boeing Service Letter No. 138A covers this same subject.) B. (P/N 15-22594) Compliance required as indicated. 1. Thoroughly inspect the nose landing gear terminal P/N 15-22594, for cracks in the trapezoidal cutout as soon as practicable, but not later than November 1, 1952, unless already accomplished, and continuing at periodic intervals not to exceed 800 hours thereafter. This cutout is visible by removing the cover plate on the lower end of the strut and turning the nose gear segment. If cracks are found, the strut may be reworked in accordance with item 2 below, and provided cracks are removed, strut may be returned to service. 2. If not already accomplished, at the next landing gear overhaul, grind the sides of the trapezoidal cutout to a 0.50 inch radius at corners to conform to the sketch shown in Boeing's Service Letter 148A. The inspection of item 1 above must also be continued after rework until service experience shows that further cracking will not occur.
86-06-07: 86-06-07 SHORT BROTHERS, LTD.: Amendment 39-5262. Applies to Short Brothers, Ltd., Model SD3-60 airplanes, serial numbers SH 3601 through SH 3665 inclusive, certificated in any category. Compliance is required within 90 days after the effective date of this AD, unless previously accomplished. 1. To prevent control system interference, install extended and additional guards in accordance with Short Brothers, Ltd., Service Bulletin SD360-27-04, dated March 1985. 2. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 3. 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 inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtaincopies upon request to Shorts Aircraft, 1725 Jefferson Davis Highway, Suite 510, Arlington, Virginia 22202. 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 becomes effective May 2, 1986.
66-23-02: 66-23-02 SENSENICH: Amdt. 39-289 Part 39 Federal Register September 22, 1966. Applies to All Fixed-Pitch Metal Propeller Models with Water-Soluble Mid-Blade Decals. Compliance required within the next 20 hours' time in service after the effective date of this AD, unless already accomplished. To prevent further mid-blade propeller failures resulting from corrosion pits that initiate fatigue cracks under the water-soluble mid-blade decal, accomplish the following: (a) Soak water-soluble mid-blade decals (Sensenich Propeller Bulletin No. R-12 describes decals) with paint remover and rub off with a rag. (Scraping or sanding of decals may inadvertently obscure evidence of possible corrosion.) (b) Apply dye penetrant to the mid-blade area and inspect for corrosion and cracks with a glass of at least three power. (c) Remove corrosive pits 0.015 inch deep or less by sanding with a 220 grit wet or dry abrasive paper and polishing with a paper of 320 grit or finer.(d) Clean area thoroughly and reinspect in accordance with (b) to insure that the removal of all corrosive pits has been accomplished. Clean and spray repaired area with a clear lacquer. (e) Replace before further flight any propeller having corrosive pits 0.015 inch deep or greater or having cracks with a propeller of the same model number that has been inspected and repaired as necessary in accordance with this AD. (Sensenich Propeller Bulletins Nos. R-11, dated March 1, 1966; R-12 dated August 1, 1966, and R-12A dated February 6, 1967, pertain to this subject.) This supersedes AD 66-11-03. This directive becomes effective October 1, 1966. Revised May 16, 1967.
2007-12-05: We are adopting a new airworthiness directive (AD) for the products listed above. 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: From airplanes that have installed the Auxiliary Fuel Tank Optional Design Change (O[Auml]M) No. 42-056, three in-service failures of the auxiliary fuel tank venting system have been reported. These failures have led to the inability to supply the complete auxilliary fuel quantity to the main tanks and the collapse of the auxilliary tank. It is suspected that the vent lines were obstructed either by ice accretion under certain climatic conditions or by blockage of the vent valves because of fuel contaminants. Undetected malfunctions of the venting system and damaged auxiliary fuel tanks may lead to a lower usable fuel quantity, subsequent fuel starvation and/or fuel spillage into the nacelle. We are issuing this AD to require actions to correct the unsafe condition on these products.