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48-11-05: 48-11-05 BELL: Applies to Model 47B Series. Compliance required at next 25-hour inspection. To provide increased strength, install main rotor drag brace, Bell P/N 47-110-146-2, in place of the existing part. (Bell Service Bulletin 47C31 also covers this subject.)
2017-10-17: We are superseding Airworthiness Directive (AD) 2014-16-19 for all Airbus Model A330-200 Freighter, -200, and -300 series airplanes. AD 2014-16-19 required revision of the maintenance or inspection program to include certain fuel airworthiness limitations. This new AD requires revision of the maintenance or inspection program, as applicable, to include new fuel airworthiness limitations. This new AD also removes certain airplanes from the applicability of AD 2014-16-19. This AD was prompted by the issuance of more restrictive fuel airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
59-12-02: 59-12-02 LOCKHEED: Applies to All Models 049, 149, 649, 749 and 1049 Series Aircraft. Compliance required as indicated. The following inspections have been established as a result of recently found corrosion and cracking on the wing Station 80 bathtub fittings, P/N's 251245 and 251246 on Model 049, 149, 649, 749 Series aircraft and Model 1049-54 aircraft and P/N's 310008 and 310009 on the remaining Model 1049 Series aircraft. These inspections shall be accomplished on all aircraft which have accumulated 12,000 or more flight-hours. Inspect affected aircraft at the next block overhaul or within 4,000 flight-hours, whichever occurs first. Inspect all aircraft for cracked bathtub fittings as follows: (1) Inspection may be made by removing the wing-to-fuselage fillet and dye checking the forward and aft edges on the neck of the bathtub fittings lugs of both the inner and stub wing fittings. (2) Replace any cracked bathtub fittings. Inspect each inner wing andstub wing Station 80 fitting for corrosion as follows: (1) Visually inspect the inner and stub wing Station 80 joint bathtub fittings adjacent to the DD8 rivets and rivet attachments taking particular care to note any imperfections or paint defects. Probe further whenever defects in paint are discovered in order to detect any corrosion. (2) Replace any wing Station 80 bathtub fittings on which corrosion cleanup exceeds a depth of 0.025-inch or a diameter of 0.70 inch (approximate diameter of a dime) around rivet attachments. Remove corrosion if within the allowable and treat per Lockheed Report 8882, (also 7789 and 5886) paragraph 1-67N, revised July 15, 1957, or equivalent. (3) Inspect the stub wing and inner wing skin upper surface for corrosion around the bathtub fitting screw holes. Also inspect the stub wing and inner wing upper skin lower surfaces between corrugations for corrosion. Maximum allowable skin cleanup without resorting to a doubler repair is 0.020-inch deep or an area not exceeding one inch wide and three inches long, provided screw holes are not enlarged. Areas of skin corrosion exceeding these allowable limits should be repaired in accordance with applicable Structural Repair Manual procedures. Clean up and protect corroded areas per Lockheed Report 8882, (also 7789 and 5886) revised July 15, 1957, or equivalent. It must be determined that any corrosion is confined to the skin only and does not penetrate into the corrugations. Reinstall all screw attachments flush in to the cleaned up areas. (4) Inspect the bathtub fitting end lugs for corrosion. Maximum permissible combined depth of corrosion on mating fitting lugs should not be such as to increase the total gap between mating faces in excess of 0.020 inch. Replace fittings which cannot be cleaned up within this tolerance. The special inspection note above may be extended an additional 12,000 flight-hours for each wing on which all fittings are replaced. Otherwise reinspection at 4,000 flight-hour periods or block overhaul whichever occurs first is required to insure detection of cracked or corroded Wing Station 80 bathtub fittings or attachments. (Lockheed Service Letter FS/231053 covers this same subject.)
87-09-01: 87-09-01 MESSERSCHMITT-BOLKOW-BLOHM GmbH (MBB): Amendment 39-5616. Applies to Models BO-209-150FV, -150RV, -160FV, -160RV, and -150FF "MONSUN" airplanes (all serial numbers) certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude inflight wing separation, accomplish the following: (a) Before further flight: (1) Inspect and modify the wing spar carry-through lower cap strip in the fuselage area in accordance with the "Inspection of Wing Spar Carry-Through" paragraph of MBB Technical Instruction No. 209-1/87, dated January 26, 1987 (hereinafter referred to as MBB TI No. 209-1/87), and the manufacturer's maintenance manual procedures, as follows: (i) Jack up the airplane and remove both main landing gear struts. (ii) Remove both landing gear brackets, Part Number (P/N) 209-21233 and P/N 209-21243. (iii) Drill out the rivets (four each) on each side of the right and left-hand elongated holes (the passage for the landing gear strut through the wing spar carry-through). (iv) Examine the surface quality adjacent to each elongated hole and the associated four rivet holes, and remove any visible flutes or score marks by polishing. (v) Carry out an ultrasonic test of the area adjacent to the elongated holes for cracks. If any crack is detected, accomplish paragraph (b) of this AD. (vi) Carry out an eddy current test of the area adjacent to the associated rivet holes for cracks. If any crack is detected, accomplish paragraph (b) of this AD. (vii) Modify the four rivet holes adjacent to each of the above-mentioned elongated holes by reaming out the rivet holes, consolidating the rivet hole walls, re-reaming the holes, and inserting HI-LOK helical rivets, in accordance with instructions contained in MBB TI No. 209-1/87. (viii) Reinstall the landing gear brackets, P/N 209-21233 and P/N 209-21243. (ix) Replace unserviceable rubber bearings, P/N 209-51003.02, with new serviceable parts. (x) Reinstall the main landing gear struts. CAUTION: During reinstallation of the struts, scoring of the surface adjacent to the elongated holes of the spar carry-through must be avoided. If scoring damage occurs, repeat steps (a)(1)(iv) through (a)(1)(vi) of this AD. (2) Carry out an ultrasonic test for cracks in the transition radii of the fuselage mounted wing attachment brackets in accordance with instructions contained in MBB TI No. 209-1/87. If any crack is detected, accomplish paragraph (b) of this AD. (3) Visually inspect for cracks or deformation of the forward and aft frame plates which form the forward and aft metal webs of the wing spar carry-through in the adapter structure to the wing stub in accordance with instructions contained in MBB TI No. 209-1/87. If any crack is detected, accomplish paragraph (b) of this AD. (4) The inspection, corrective action, and modification specified in paragraph (a) of this AD must be performed at an appropriately rated FAA repair station by personnel specifically training by MBB. (b) If any crack is detected, before further flight, accomplish the following: (1) Inform the manufacturer at the address listed below of the crack(s) found. (2) Request a manufacturer repair procedure approved by the FAA. (3) Incorporate the FAA approved repair procedures. (c) Prior to further flight: (1) Change the "LIMITATIONS" section of the FAA approved Model BO-209 "MONSUN" Approved Flight Manual (AFM) using pen and ink, and operate the airplane in accordance with these limitations as follows: (i) Paragraph 2.9.2 of the AFM, change "above" to "up to," to read as follows: "Utility Category: Spinning with flaps retracted, lazy eights, chandelles, steep turns up to 60 degree bank." (ii) Paragraph 2.12.9 of the AFM, change "above" to "up to" in Section 2. "Utility Category" to readas follows: "2. Utility Category ... lazy eight up to 60 degree bank ..." (2) Fabricate and install on the canopy center line strip, visible to the pilots, the following placard using letters of a minimum 0.10 inch in height: "ACROBATIC FLIGHT PROHIBITED". (3) Modify the limitations placard mounted on the canopy center line strip by permanently deleting or obliterating the following words: "Only if accelerometer is installed: Slow roll 125 Kt, wing over, loop 135 Kt, steep turns above 60 degree bank 117 Kt." NOTE: The placard required by paragraph (c)(2) of this AD may be mounted in a suitable manner to cover the above-stated text to satisfy this requirement. (d) Upon accumulating 3000 hours time-in-service (TIS) and every 500 hours TIS thereafter, carry out an ultrasonic test of the wing spar carry-through lower cap strip area adjacent to the elongated holes and the associated four rivet holes with HI-LOK rivets for cracks in accordance with the MBB Technical Note 209-1/87, page 3, dated January 22, 1987. If any crack is detected, before further flight, accomplish the repairs specified in paragraph (b) of this AD. (e) If a ferry flight to an approved maintenance location is required: (1) Airplanes not previously used for acrobatics may be flown to the location in accordance with FAR 21.197. (2) Airplanes previously used for acrobatics must be visually inspected for cracks prior to the ferry flight in accordance with the "sketch" (page 4 of 4) of the MBB Technical Note No. 209-1/87, dated January 22, 1987. If any crack is found, further flight is prohibited until all actions of paragraphs (a) and (b) of this AD are accomplished. (f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Messerschmitt-Bolkow-Blohm GmbH, Department 1QS 143, Post fach 801160, D-8000 Munchen 80, Federal Republic of Germany; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5516, becomes effective on May 6, 1987.
2001-22-18: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce, plc models Tay 650-15 and 651-54 turbofan engines. This amendment requires initial and repetitive visual and ultrasonic inspections of fan blades for cracks, and, if necessary, replacement with serviceable parts. In addition, this AD requires recording instances when engines are operated in a stabilized manner in newly prohibited ranges. This amendment is prompted by reports of fan blade failures. The actions specified by this AD are intended to prevent fan blade failures, which can result in an uncontained engine failure, engine fire, and damage to the airplane.
75-11-04: 75-11-04 UNITED AIRCRAFT: Amendment 39-2207. Applies to all United Aircraft of Canada Limited PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28, -34 series turbo-prop engines and PT6B-9 turboshaft engines, incorporating an unmodified power turbine shaft housing assembly part number 3010548. Compliance required as indicated. To aid the early detection, and thereby prevention of PT6A or PT6B engine distress especially in the reduction gearbox of engines incorporating power turbine shaft housing assembly part number 3010548 yet unmodified, accomplish the following: For the PT6A-20, -20A, -20B, -6/C20 engines affected, compliance required within the next fifty hours in service after effective date of this AD. For the PT6A-6, -6A, -6B, -27, -28, -34 and PT6B-9 engines affected, compliance required at the next engine overhaul shop visit, but no later than 3500 hours in service after effective date of this AD. 1. Unless previously accomplished, remove the reduction gearbox oil drain plug part number MS9015-08 and discard the preformed packing part number MS9388-115. Install magnetic chip detector part number 3014794 or 3019373 with a new preformed packing part number MS9388-115 and torque to 45 to 55 lb. in. and lockwire. Install cap part number MS25043-12D or connector part number MS3106-R-12S-3S with connected electrical wiring suitably supported and leading out to a more accessible area within the engine nacelle enclosure. 2. Within the next twenty-five hours in service after installation of the magnetic chip detector and every twenty-five hours in service thereafter, check magnetic chip detector for electrical continuity using any utility ohmmeter. If a resistance of 100 ohms or less is indicated, remove and clean the magnetic chip detector, and inspect the main engine oil filter in accordance with AD 75-06-01. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this Airworthiness Directive. This amendment is effective May 20, 1975.
87-03-06 R1: 87-03-06 R1 BEECH: Amendment 39-5513 as amended by Amendment 39-5557. Applies to Model 99, 99A, A99A, B99 and C99 (Serial Numbers U-1 thru U-240); 100 and A100 (Serial Numbers B-1 thru B-247); and B100 (Serial Numbers BE-1 thru BE-137), airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To detect looseness of the elevator outboard hinge attachment to the stabilizer and prevent loss of integrity of the hinge attachment, accomplish the following: (a) Upon the accumulation of 1000 hours total time-in-service (TIS) or within the next 100 hours TIS after the effective date of this AD, whichever comes later, and thereafter at intervals not to exceed 100 hours TIS for Model 99 Series or 150 hours TIS for Model 100 Series airplanes, visually inspect each elevator outboard hinge attachment as follows: (1) Hold the elevator steady at the trailing edge. (2) Push up and down onthe elevator leading edge and visually inspect for movement of the elevator hinge bearing bracket. (b) If movement of the hinge bearing bracket is detected in (a)(2) above, prior to further flight, replace the hinge attach rivets with bolts in accordance with the instructions in Beech Service Bulletin No. 2132, revised December 1986. (c) Unless previously required by paragraph (b) of this AD, on all airplanes with more than 1000 hours total TIS, within the next 600 hours TIS after the initial inspection required by paragraph (a) of this AD, install bolts in place of the four hinge attach rivets in accordance with the instructions in Beech Service Bulletin No. 2132 revised December 1986. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after bolts have been installed per paragraphs (b) or (c). (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (f) The repetitive inspection intervals, required by this AD may be adjusted up to 10 percent of the specified interval so as to coincide with other scheduled maintenance. (g) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, 9709 East Central, P.O. Box 85, Wichita, Kansas 67201; or the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5513 became effective on February 20, 1987. This amendment, 39-5557, becomes effective March 12, 1987.
2017-10-20: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. This AD was prompted by fatigue cracking in the fuselage station (FS) 332.00 bulkhead common to the horizontal stabilizer front spar attachment. This AD requires repetitive inspections to detect cracks in the bulkhead and any necessary repairs. This AD also provides an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. We are issuing this AD to correct the unsafe condition on these products.
2017-09-09: We are adopting a new airworthiness directive (AD) for certain Zodiac Seats California LLC seating systems. This AD was prompted by a determination that the affected seating systems may cause serious injury to the occupant during forward impacts when subjected to certain inertia forces. This AD requires removing affected seating systems. We are issuing this AD to address the unsafe condition on these products.
2001-22-16: This amendment supersedes Airworthiness Directive (AD) 95-02-18, which applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C (C-12J), and 1900D airplanes. AD 95-02-18 requires you to repetitively inspect the engine truss assemblies for cracks, repair or replace any cracked engine truss assembly, and install reinforcement doublers. This AD requires engine truss assembly replacement, periodic inspections and replacements, and the eventual incorporation of a cowling support installation kit as terminating action. The repetitive inspections of AD 95-02-18 will be retained until mandatory engine truss assembly replacement. This AD is the result of continued reports of fatigue cracks found on engine trusses on airplanes in compliance with AD 95-02-18. The actions specified by this AD are intended to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.