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87-24-11: 87-24-11 GARRETT TURBINE ENGINE COMPANY: Amendment 39-5781. Applies to Garrett Model GTCP 85 series Auxiliary Power Units equipped with one-piece cast turbine wheels, Part Nos. 968095-X, 3604604-X, 3606982-1, and 3842072-1. Compliance required as indicated, unless previously accomplished. To prevent turbine wheel separation and resulting containment shroud fragmentation, accomplish the following: A. Install the augmentation containment ring, part number 3612249-1, in Garrett Model GTCP 85 series auxiliary power units in accordance with the accomplishment instructions of Garrett Service Bulletin GTCP 85-49-5689, dated July 24, 1987, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region, as follows: 1. On in-flight operable units, within 18 months after the effective date of this AD. 2. On ground-operable-only units, within 36 months after the effective date of this AD. B. Installation ofthe Hastelloy S turbine shroud, in accordance with Garrett Service Bulletin 85-49-700, dated July 20, 1987, or later FAA approved revisions, is considered an acceptable alternate means of compliance with this AD. C. An alternate means of compliance with this AD which provides an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base 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 Garrett Aviation Services Company, Data Distribution, Department H64-5, P.O. Box 29003, Phoenix, Arizona 85038. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective January 13, 1988.
90-10-01: 90-10-01 AEROSPATIALE (FORMERLY SUD AVIATION/SUD-SERVICE): Amendment 39-6585. Docket No. 90-NM-03-AD. Applicability: All Aerospatiale Caravelle Model SE 210 Model series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect fatigue cracks in the wing-to-fuselage junction and fuselage lower section components, accomplish the following: A. Prior to the accumulation of 29,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, perform one of the following inspections in accordance with Aerospatiale Service Bulletin 53-51, Revision 6, dated July 31, 1986: 1. Visual inspection of the wing-to-fuselage junction fittings at Frames 31 and 35, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings; or 2. Visual and eddy current inspection of the wing-to-fuselage junction fittings at Frames 31and 35, and a magnetic particle inspection of all removed horizontal bolts, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 7,500 landings. B. If cracks or sheared bolts or rivets are detected during the inspection required by paragraph A., above, replace with serviceable parts prior to further flight, in accordance with Aerospatiale Service Bulletin 53-51, Revision 6, dated July 31, 1986. Repeat inspections thereafter at intervals specified in paragraph A., above. C. Prior to the accumulation of 29,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,500 landings, perform a visual and dye penetrant inspection of the fuselage lower section beam under Rib 52, the attachment fittings at the rear section of Rib 52, and the front pick-up fittings between the beam under Rib 52 and the canted frames at Frame 30, in accordance with Aerospatiale Service Bulletin 53-52, Revision 7, dated March 22, 1988. D. If sheared-off attachment hardware is detected during the inspection required by paragraph C., above, prior to further flight replace with serviceable parts in accordance with the Structural Repair Manual, Chapter 57-1-33. Repeat the inspection identified in paragraph C., above, at intervals not to exceed 2,500 landings. E. If cracks are detected during the inspection required by paragraph C., above, in Fittings 210.12.52.382/383 and 210.22.53.012 at the attachment level, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. Repeat the inspection identified in paragraph C., above, at an interval to be approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. F. If cracks are detected during the inspection required by paragraph C., above, in Fittings 210.12.52.382/383 and 210.22.53.012 outside the attachment areas, prior to further flight, replace with new fittings, in accordance with Aerospatiale Service Bulletin 53-52, Revision 7, dated March 22, 1988. Repeat the inspection identified in paragraph C., above, at intervals not to exceed 2,500 landings. G. An 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, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region. NOTE: 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, Standardization Branch, ANM-113. H. 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 mayobtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6585, AD 90-10-01) becomes effective on June 1, 1990.
47-11-02: 47-11-02 NAVION: (Was Mandatory note 2 of AD-782-3.) Applies to All Models Equipped With Hartzell HC12x20-1 Propeller Hubs and 8628 Blades. To be accomplished not later than May 1, 1947. Vibration tests of the Hartzell HC12x20-1 propeller with these airplanes indicate that the propeller diameter should be reduced from 86 inches to 84 inches. This is accomplished by cutting 1 inch from the tip of each 8628 blade, and making the shortened blade 18428R. This blade rework must be performed either by the Hartzell factory or by a certified propeller repair agency. (Par. B of North American Field Service Bulletin No. 20 dated January 28, 1947, covers this rework.) Upon compliance with this AD, the presently required placard against engine operation between 1,950 and 2,150 r.p.m. and over 2,250 r.p.m. may be removed.
90-05-03: 90-05-03 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6520. Docket No. 89-NM-236-AD. Applicability: de Havilland Model DHC-8-300 series airplanes, Serial Numbers 100 through 231, inclusive, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent possible rupture of the engine bleed air ducts, accomplish the following: A. Within the next 50 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours time-in-service, perform a visual inspection to detect cracks or complete separation of the bleed air precooler mounting lugs, in accordance with de Havilland Alert Service Bulletin A8-21-32, Revision A, dated November 22, 1989. B. If cracks are found in more than one lug, or if any lug has completely separated, repair prior to further flight, in accordance with de Havilland Alert Service Bulletin A8-21-32, Revision A, dated November 22, 1989.C. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: 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, Standardization Branch, ANM-113. D. 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 information from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South,Seattle, Washington, or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment (39-6520, AD 90-05-03) becomes effective on April 6, 1990.
77-03-01: 77-03-01 ROCKWELL: Amendment 39-2823. Applies to Models 690, 690A, and 690B, S/N's 11000 through 11371. Compliance required as indicated. Before further flight, unless already accomplished, except that the airplane may be flown in accordance with FAR 21.197 to a base where the inspection or repair may be performed, accomplish the following: Inspect both left and right wing rivets in accordance with Rockwell Service Bulletin No. 163 dated January 21, 1977, or later approved revision or in accordance with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. (a) If no loose or sheared rivets are found, reinspect at 25-hour intervals or after any unusually hard landing, in accordance with Rockwell Service Bulletin No. 163 dated January 21, 1977, or later approved revision or in accordance with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. (b) If loose or sheared rivets are detected, repair and reinspect in accordance with the procedures described in Rockwell Service Bulletin No. 163 dated January 21, 1977, or later approved revision or in accordance with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. (c) Within 500 hours' time in service after the effective date of this AD, rework all designated rivet patterns in accordance with (b) above. When all patterns have been reworked in accordance with (b), the repetitive inspections of (a) and (b) may be discontinued. This amendment becomes effective February 16, 1977, and is effective upon receipt for all recipients of the AD dated January 27, 1977, which contained this amendment.
71-16-04: 71-16-04 LEARJET: Amdt. 39-1255. Applies to Models 23 (S/N 23-003 through 23- 099); 24 (S/N 24-100 through 24-247); and 25 (S/N 25-002 through 25-080) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent battery temperature and charging conditions that can result in battery fires and in intense heat, accomplish the following: A) Prior to the next flight conduct a one-time inspection of both batteries for: 1) Heat damage, and if any heat damage is found, replace the damaged battery with an airworthy one. 2) The presence of marathon (sonotone) batteries, Model CA20H or CA21H and for the type of cells (polystyrene, nylon or a combination thereof) contained in said batteries. NOTE: Polystyrene cells can be identified by their clear or slightly yellow plastic appearance. All marathon batteries manufactured prior to 1969 contained polystyrene cells. Marathon batteries manufactured in 1969 or later, contain nylon cells which are identifiable by their milky white or bluish appearance. All marathon batteries rebuilt since new may contain a mixture of polystyrene and nylon cells. B) Within ten (10) hours' time in service after the effective date of this AD, on those aircraft having marathon (sonotone) batteries Models CA20H or CA21H containing either all polystyrene cells or a combination of polystyrene and nylon cells, and within fifty (50) hours' time in service after the effective date of this AD and on those aircraft having other approved batteries or sonotone batteries containing all nylon cells install Learjet Modification Kit No. AMK 71-10 or any equivalent modification submitted to and approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, and thereafter operate the aircraft in accordance with the flight manual revision provided with the kit. NOTE: If polystyrene battery cells are replaced with nylon battery cells, the aircraft need not be modified within 10 hours' but may be operated up to 50 hours' time in service after the effective date of this AD. C) Until Paragraph B is accomplished if any ground operation discloses a weak battery, prior to further flight, check both aircraft batteries in accordance with applicable Learjet Service Manual instructions and make needed battery repairs or replacement and conduct all flight operations in accordance with Learjet Service Bulletin 23/24/25-224 dated April 14, 1971. NOTE: The Service Bulletin was incorrectly cited as 23/24/25-225 in the air mail letter dated July 20, 1971. This amendment becomes effective August 3, 1971, to all persons except those to whom it was made effective by letter dated July 20, 1971.
96-11-15: 96-11-15 DORNIER: Amendment 39-9655. Docket 96-NM-109-AD. Applicability: All Model 328-100 series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been otherwise modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent restriction of the flightcrew's ability to see through the windshields due to shattering or cracking of the windshields, and to continue to control the airplane safely; accomplish the following: (a) For airplanes on which a windshield having Part Number (P/N) 001A561A0000204 is installed on the left-hand side of the cockpit, or on which a windshield having P/N 001A561A0000205 is installed on the right-hand side of the cockpit: Within 24 hours after receipt of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM. "Flight above 10,000 feet mean sea level (MSL) is prohibited." (b) For all airplanes: Within 45 days after receipt of this AD, replace any windshield having P/N 001A561A0000204 (left-hand side), or P/N 001A61A0000205 (right-hand side); with a new windshield having P/N 001A561A0000200 (left-hand side), or P/N 001A561A0000201 (right-hand side); in accordance with Dornier Service Bulletin SB-328-56-165, dated April 19, 1996. Following this replacement, the AFM limitation required by paragraph (a) of this AD may be removed. (c) For all airplanes: Within 24 hours (clock hours, not flight hours) following any incident of shattering or cracking of either front windshield, submit a report containing the serial number of the airplane and the part number of the affected windshield to: Connie Beane, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056; fax (206) 227-1149. This reporting requirement is applicable to findings on all windshields, including the replacement windshields required by paragraph (b) of this AD. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB control number 2120-0056. (d) As of the date of receipt of this AD, no person shall install a windshield having P/N 001A561A0000204 (left-hand side), or P/N 001A561A0000205 (right-hand side), on any airplane. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (f) Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The replacement shall be done in accordance with Dornier Service Bulletin SB-328-56-165, dated April 19, 1996. 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 Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on June 17, 1996, to all persons except those persons to whom it was made immediately effective by emergency AD 96-11-15, issued May 24, 1996, which contained the requirements of this amendment.
50-12-01: 50-12-01 HAMILTON STANDARD: Applies to All Aircraft Equipped With Continental Engines, Models W-670-6A (R-670-3, -5), W-670-6N (R-670-4), W-670-16 (R-670-8, -11, - 11A) and Hamilton Standard Ground Adjustable Propellers Having Blades, Model 11C1 (Navy 4350, 4350F, 4350F1). Compliance required not later than April 15, 1950. To minimize the possibility of propeller blade shank fatigue failures as a result of noncompliance with a mandatory engine operation restriction, the following precautionary measures should be taken: (1) Check the marking on the engine tachometer and correctly mark it, if necessary, with a red arc which covers the entire r.p.m. range above the higher side of the 1,900 r.p.m. graduation. (2) Install placard in aircraft to read: "Avoid all engine operation above 1,900 r.p.m. except during takeoff". (3) Check position of the propeller and correctly index, if necessary, in the zero degree position (blades in line with crankthrow).
80-21-09 R1: 80-21-09 R1 BELL: Amendment 39-3942 as amended by amendment 39-3976. Applies to all Model 47 series helicopters and military Model H-13, OH-13, and TH-13T series helicopters, including modified versions, certificated in all categories, that are equipped with the 47-641-170 series tail rotor hub and blade assemblies (Airworthiness Docket No. 80-ASW-29). Compliance required within 100 hours' time in service after November 17, 1980. To prevent loss of directional control as a result of possible tail rotor pitch link failure, accomplish the following, unless already accomplished in accordance with Bell Helicopter Textron Alert Service Bulletin No. 47-80-5, Rev. A, dated April 29, 1980. (a) Remove the tail rotor pitch link from each blade pitch horn. (b) Inspect the pitch link bearings for axial and radial play. Remove bearings having .015 inch or more of play or looseness, and install serviceable bearings. (c) Install bolts P/N NAS1304-32D or 20-057-4-32D (used with pitch horn, P/N 47-641-187-1, -3, or -5), or P/N NAS1304-30D, or 20-057-4-30D (used with pitch horn, P/N 47-641-187-7) as appropriate, with washer, P/N 47-641-189-1 or -3 under the bolt head or nut, and washer P/N 47-641-189-3 between the link bearing and pitch horn with bevel towards the bearing. Torque nuts 80 to 100 inch-pounds and install cotter pins. (d) Determine that no binding or interference occurs in the blade controls when the tail rotor controls are full left and right, and the tail rotor hub is flapped to each stop. Track the tail rotor blades in accordance with the appropriate Model 47 maintenance manual if a rod end bearing or a link is replaced in accordance with paragraph (b) of this AD. (e) Equivalent means of compliance with this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, FAA, Southwest Region. (Bell Helicopter Textron Operations Safety Notice OSN 47-79-1 dated October 19, 1979, also pertains to this subject.) Amendment 39-3942 became effective November 17, 1980. This amendment 39-3976 becomes effective November 24, 1980.
47-21-13: 47-21-13 REPUBLIC: (Was Mandatory Note 3 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 to 234, Inclusive. Compliance required prior to July 1, 1947. Inspect the rivets of the forward end of the elevator control push-pull tube in front of the instrument panel for size, looseness and replacement as necessary. If the installation has been made with four 5/32-inch diameter rivets, replace with six 3/16-inch rivets (3 on each side evenly spaded). If four 3/16-inch diameter rivets are already installed and looseness exists, replace the loose rivets and install two additional 3/16-inch rivets (one on each side evenly spaced). (Republic Seabee Service Bulletin No. 6 dated January 16, 1947, covers this same subject.)