Results
58-18-03: 58-18-03 VICKERS: Applies to All Viscount 700 Series Aircraft. Compliance required by November 1, 1958. Following a recent case of damage to Nos. 1 and 2 flaps, beams and telescopic rods caused by a flap chain tensioner barrel becoming completely unscrewed on No. 1 flap chain, Vickers-Armstrongs recommends the wirelocking of flap chain tensioners on Nos. 1, 2 and 3 flaps. The British Air registration Board considers this mandatory. The FAA concurs with this action and considers compliance therewith mandatory. (Vickers-Armstrongs Modification D.2554 covers this subject.)
70-12-11: 70-12-11 BRITTEN-NORMAN, LTD: Amdt. 39-1006. Applies to BN-2 and BN-2A airplanes, serial numbers up to and including S/N C231. Compliance is required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of the flap actuating system, replace flap lever drive attachment bolt P/N A111-6G with a serviceable bolt, P/N A111-9G, and replace the flap center operating lever P/N NB-45-D-997 with either - (1) A serviceable flap center operating lever P/N NB-45-D-997 modified and remarked as P/N NB-45-D-2173 (MOD.NB/M/417) in accordance with Britten Norman Modification Leaflet No. BN-2/NB/M/417, Part 2, Issue 1, dated April 8, 1970, or a later ARB- approved issue or an FAA-approved equivalent; or (2) A serviceable flap center operating lever P/N NB-45-D-2173. This amendment becomes effective June 11, 1970.
69-08-04: 69-08-04 BRITISH AIRCRAFT CORPORATION: Amdt. 39-748. Applies to Model BAC 1-11, 203/AE and 204/AF airplanes. Compliance required within the next 2500 hours' time in service after the effective date of this AD, unless already accomplished. To prevent fuel leakage into the wing center section torque box area, replace the aluminum alloy refuel/defuel valve housing P/N AB 45A101 with modified stainless steel valve housing P/N AB 45A1239 in accordance with BAC 1-11 Service Bulletin No. 28-PM 924 or later ARB-approved issue or FAA-approved equivalent. This amendment becomes effective May 11,1969.
46-13-04: 46-13-04 DOUGLAS: (Was Service Note 10 of AD-618-3 and Service Note 11 of AD-669-3.) Applies to All DC3 Models Except Conversions From the C-47 Series. \n\n\t1.\tInspect visually for cracks all landing gear rear brace strut fittings, P/N 230659, that have not been removed and magnetically inspected at last airplane overhaul. This inspection should be accomplished prior to next flight. \n\n\t2.\tIf crack is less than 1/8-inch long it may be ground or filed out, being careful to remove all marks and scratches, without removing the fitting, until the next overhaul. If cracks are found to be longer than 1/8 inch, the fitting must be removed and repaired in accordance with paragraph 3 below. \n\n\t3.\tCracks in weld area can be repaired by grinding away all existing weld and rewelding. If cracks extend through spacer plate, the spacer plate may be cut back beyond the end of crack, all old weld removed, and a new section of spacer plate lap welded to the remaining portion of the spacer plate and then seam welded to the side plates. Cracks extending through the side plates for a maximum of 1/4 inch may be repaired by grinding a "V" on the outside surface of the plate to a minimum of 1/16 inch beyond the end of the cracks and welding. The weld must be ground smooth. \n\n\t4.\tIf fitting is removed, rivets may be replaced with spacers and 3/16-inch AN bolts having a ream fit through the bulkhead and fitting in order to facilitate installation. \n\n\t5.\tIn order to insure that parts in the airplane continue to remain satisfactory for service, the following inspection procedure should be followed: \n\n\t\t(a)\tVisually inspect landing gear rear brace strut fitting at periods not to exceed 1,000 hours. \n\n\t\t(b)\tRemove and magnetically inspect rear brace strut fitting at each major overhaul. \n\n\t(The inspection and repair outlined above are covered by Douglas Service Bulletin No. 233, Section IV.). \n\n\tThe inspections outlined above will not be necessary when the landing gear rear brace strut fitting, P/N 230659, is replaced by the new fitting, P/N 4341810. \n\n\t(Supplement to Douglas Service Bulletin No. 233, as revised October 24, 1946, covers this same subject.)
47-50-04: 47-50-04 STINSON: Applies to L-5 Series Aircraft. Compliance required as soon as possible but not later than March 1, 1948. To prevent loss of elevator control, the elevator push-pull tube assemblies, P/N 76-62204, should be inspected for security and proper staking of nut which secures rod end and D-4 bearing in housing P/N 76-62206. If there is no cotter pin securing this nut, it should be staked to the rod in at least three places.
47-02-02: 47-02-02 DOUGLAS: (Was Mandatory Note 10 AD-762-7.) Applies to All C-54 Series Aircraft and DC-4 Aircraft, Serial Numbers 42904 to 42943, Inclusive; 42948 to 42952, Inclusive; 42982 to 42996, Inclusive; and 43065. \n\n\tTo be accomplished not later than July 1, 1947. \n\n\tInspect the clevis shear bolts in the vertical stabilizer forward attach fitting (Station 953), P/N 4106204 and -1, for loose or stretched bolts. In some instances, the lower 3/16-inch bolts, when being checked for tightness, have broken. In order to overcome the difficulty, the stabilizer attaching fittings should be reworked and bolts be replaced with high heat-treated bolts. \n\n\t(Douglas Service Bulletin DC-4 No. 11, covers this same subject.)
73-12-01: 73-12-01 BELL: Amendment 39-1650. Applies to Model 206A and 206B helicopters, serial numbers 4 through 865 and 867 through 873, certificated in all categories, equipped with vertical fin, P/N 206-020-113-5, -7 and -9. Compliance required within the next 25 hours' time in service after the effective date of this A.D., unless already accomplished within the last 25 hours' time in service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. To detect possible fatigue cracks in the skin of the vertical fin in the area of the tail boom attachment, accomplish the following: (a) Remove all tail fairing assemblies to gain access to the inboard side of the vertical fin assembly. (b) Visually inspect the inboard skin of the vertical fin in the area of attachment for any cracks, paying particular attention to the area aft of the upper rear attachment insert. (c) If any crack is found greater than 3.5 inches in length, removeand replace the fin before further flight. (d) If any crack is found less than 3.5 inches in length, remove and replace or repair the fin in accordance with Part II of Bell Helicopter Company Service Letter No. 206-203, Revision C, dated March 14, 1973, or later FAA approved revision, before further flight. (e) If no cracks are found, continue the repetitive inspections specified above. (f) This A.D. is no longer applicable when the fin is modified in accordance with Part I or II of Bell Helicopter Company Service Letter No. 206-203, Revision C, dated March 14, 1973, or later FAA approved revision. (Bell Helicopter Company Service Bulletin No. 206-01-73-1, dated January 9, 1973, pertains to this subject.) This amendment becomes effective July 1, 1973.
47-50-05: 47-50-05 AERONCA, CHAMPION. PIPER, SILVAIRE (LUSCOMBE): Applies to Airplanes Equipped With Edo Model 92-1400 Floats. Compliance required by February 15, 1947. To prevent the possible failure of the wirepull attachment on Edo Model 92-1400 floats, install redesigned wirepull (Edo P/N 92-S-239 on J3C-50S and J3C-65S, Edo P/N 92-S-229 on PA-11S, Edo P/N 92-S-237 and -239 on S7AC, Edo P/N 92-S-237 on S11AC, and Edo P/N 92-S-233 and -235 on Silvaire (Luscombe) 8 Series) under each of the front and rear strut attachment fittings. (Edo Service Bulletin No. 2 dated August 15, 1947, contains detailed instructions for making this change.)
47-49-12: 47-49-12 LOCKHEED: (Was Service Note 12 of AD-763-3.) Applies to All Models 49, 649, and 749 Serials Which Incorporate Short Type Metal Aft Doors for the Main Landing Gear. At periods not to exceed 250 hours inspect the metal aft doors of the main landing gear for signs of cracks in the vicinity of the forward hinge attachments. When cracks are found, satisfactory reinforcements and doublers should be installed. When doublers have been installed (doublers only are necessary if the doors are not already cracked) the periodic inspections may be discontinued. (LAC Service Bulletin 49/SB-274 covers this same subject.)
72-16-05: 72-16-05 ROLLS ROYCE (1971) LTD: Amendment 39-1491 as amended by Amendment 39-1568. Applies to Dart Series Models 506, 510, 511, 514, 525 through 529, 531, 532, and 542 engines and all variants. Compliance required as indicated unless already accomplished. To prevent engine failures resulting from fatigue cracks of the impellers specified in Column 2 of the following tables, accomplish the following: (a) Within the next 50 flights after the effective date of this AD or before the accumulation of the number of flights specified in Column 3, for the applicable impeller, whichever occurs later, and thereafter at intervals not to exceed the number of flights specified in Column 3, replace the applicable impellers specified in Column 2 when they are installed on the engines specified in Column 1 with impellers having the same part number or a part number approved for that engine which have not exceeded their life limits. (Column 1) DART ENGINE SERIES (Column 2) IMPELLERS (Column 3) LIFE LIMITS (FLIGHTS) Second stage impellers incorporating all Pre 797 Modifications 4,500 Second stage impellers incorporating Modification 797 which have not been Open Bore Processed.* 9,000 Models 506, 510, 511 and 514 and all variants First and second stage impellers incorporating Modification 797 Open Bore Processed.* 1st stage - 10,500 2nd stage - 6,000 Second stage impeller incorporating Modification 1455. 14,000 since the incorporation of Modification 1455 Second stage impellers incorporating all Pre 797 Modifications 4,500 Models 525 through 529, 531, and 532 and all variants Second stage impellers incorporating Modification 797 which have not been Open Bore Processed.* 14,000 First and second stage impellers incorporating Modification 797 Open Bore Processed.* lst stage 9,000 2nd stage - 11,000 *NOTE: For purposes of this AD "Open Bore Processed" means that the impeller during an overhaul subsequent to the incorporation of Modification 797, has been stripped and anodized or anodized, without the impeller bore being fitted with blanks, or that leakage past the blanks has occurred due to an improper fitting of the blanks. (b) Within the next 50 flights after the effective date of this amendment, (Amdt. 39-1568, effective December 4, 1972), or before the accumulation of the number of flights specified in Column 3, for the applicable impeller, whichever occurs later, and thereafter at intervals not to exceed the number of flights specified in Column 3, replace the applicable impellers specified in Column 2 when they are installed on the engines specified in Column 1 with impellers having the same part number or a part number approved for that engine, which have not exceeded their life limits. Column 1 DART ENGINE SERIES Column 2 IMPELLERS Column 3 LIFE LIMITS (FLIGHTS) Models 506, 510, 511, 514 and all variants First stage impellers incorporating Modification1455 14,000 since the incorporation of Modification 1455 Models 525 through 529, 531, and 532 and all variants First stage impellers incorporating Modification1455 11,500 since the incorporation of Modification 1455 Models 542-4 and 542-10 and all variants Second stage impellers incorporating all PreModification 1455 modifications Second stage impellers incorporating Modification 1455 Second stage impellers incorporating Modification1475 12,000 16,000 since the incorporation of Modification 1455 14,500 (c) For the purpose of complying with this AD a flight shall constitute an engine operating sequence consisting of an engine start, takeoff operation, landing and engine shut-down. The number of flights may be determined by actual count or, subject to approval, by the FAA assigned maintenance inspector, by dividing the impeller time in service by the operator's fleet average time per flight. Amendment 39-1491 became effective July 31, 1972. Thisamendment 39-1568 becomes effective December 4, 1972.
71-17-03: 71-17-03 MCCAULEY AIRCRAFT: Amendment 39-1265. Applies to following propeller models with hub serial numbers installed on Cessna 206, U206, and P206 series aircraft with Continental IO-520 series engines. PROPELLER MODELS D3A32C77/82NK-2 D3A32C88-A/82NC-2 D3A32C77-A/82NK-2 D3A32C88-F/82NC-2 D3A32C77-F/82NK-2 D3A32C88-J/82NC-2 D3A32C77-J/82NK-2 D3A32C90/82NC-2 D3A32C79/82NK-2 D3A32C90-A/82NC-2 D3A32C79-A/82NK-2 D3A32C90-B/82NC-2 D3A32C79-B/82NK-2 D3A32C90-C/82NC-2 D3A32C79-F/82NK-2 D3A32C90-F/82NC-2 D3A32C79-J/82NK-2 D3A32C90-J/82NC-2 D3A32C88/82NC-2 HUB SERIAL NUMBERS 650000 up to and including 686370 except for the following serial numbers: 685222 thru 685238 685977 thru 685982 685290 686087 685391 and 685392 686082 thru 686084 685408 686181 and 686182 685557 and 685558 686210 thru 686214 685848 thru 685855 686367 thru 686369 685907 thru 685918 Compliance required as indicated, unless already accomplished.a. Propellers with 600 or more total hours in service replace or rework hubs in accordance with paragraphs c or d within the next 25 hours in service after the effective date of this airworthiness directive. b. Propellers with less than 600 total hours in service replace or rework hubs in accordance with paragraphs c or d prior to the accumulation of 625 hours in service. c. Replace the following hubs with a serviceable hub model listed in Table IV of McCauley Service Bulletin No. 89 dated 14 May 1971 or later FAA approved revision, or with a D3A32C77-KLM, LM, or -M; D3A32C79-KLM, LM, or -M; D3A32C88-KLM, -LM, or -M, or D3A32C90-KLM, -LM or -M model: HUB MODELS D3A32C79, D3A32C79-A, D3A32C90, D3A32C90-A, D3A32C90-B HUB SERIAL NUMBERS 650000 up to and including 670855 d. Rework the following hub models in accordance with paragraph 3, page 2 of McCauley Service Bulletin No. 89 dated 14 May 1971 or later FAA approved revision, or an equivalent method approved by the Chief, Engineering and Manufacturing Division, FAA Eastern Region. D3A32C77 D3A32C88-A D3A32C77-A D3A32C88-F D3A32C77-F D3A32C88-J D3A32C77-J D3A32C90-B D3A32C79-B D3A32C90-C D3A32C79-F D3A32C90-F D3A32C79-J D3A32C90-J D3A32C88 NOTE: Cessna Service Letter SE71-15 also covers this subject. This amendment is effective August 18, 1971.
71-08-01: 71-08-01 MCDONNELL DOUGLAS: Amdt. 39-1187. Applies to DC-9 series airplanes incorporating automatically deployed emergency evacuation slides in the tailcone area. \n\n\tCompliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failure of the aft evacuation slide automatic deployment system, inspect the two attaching rivets for the evacuation slide lanyard attach plate and verify that the Douglas P/N 5924584-3 plate is attached to the tail cone ring with MS 20470AD4 (1/8 inch diameter) rivets as specified in Douglas Aircraft Company, All Operators Letter (AOL) 9-527 dated November 19, 1970 and/or Douglas Aircraft Division DC-9 Service Bulletin NO. 25-118 dated August 27, 1968, or later FAA-approved revisions. If rivets of less than 1/8 inch diameter are installed, they must be replaced with MS 20470AD4 (1/8 inch diameter) rivets or No. 8 or No. 10 corrosion resistant steel screws and locknuts, oran equivalent method of attachment as approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective April 20, 1971.
73-13-04: 73-13-04 TELEDYNE CONTINENTAL MOTORS: Amdt. 39-1651. Applies to the following Teledyne Continental Model engines: O-470-J REMANUFACTURED: S/N's 46949 through 47000; 202001 through 202060. O-470-K REMANUFACTURED: S/N's 49210 through 49302. O-470-L REMANUFACTURED: S/N's 69352 through 69491. O-470-R NEW: S/N's 451001 through 451285. REMANUFACTURED: 98501 through 99000; and 2120001 through 212289. Compliance required as indicated within the next five hours time in service after the effective date of this Airworthiness Directive. Unless already accomplished inspect the carburetor bowl 1/4" drain plug for security by applying 120 to 144 in. lbs. of torque. Caution should be exercised in order not to apply excessive torque. After proper torque has been applied, check for leakage or seepage. If seepage or leakage is present, remove drain plug and check for thread damage. Replace as necessary with airworthy parts. After accomplishment of the above, place an identifying yellow dot enamel or similar paint adjacent to the drain plug. This amendment is effective June 20, 1973, and was effective upon receipt for all recipients of the air mail letter dated May 25, 1973, which contained this amendment.
70-23-05: 70-23-05 AEROSTAR: Amdt. 39-1110. Applies to all Model 600 and 601 airplanes, serial numbers 60-0001 through 60-0056 and 61-0001 through 61-0070. Compliance required as indicated, unless already accomplished. To prevent fuel discharge into the engine compartment and possible engine fire, accomplish the following: 1. Before further flight after the effective date of this AD, inspect each of the two Edison P/N 195-10TC112D1 fuel pressure indicators for a ruptured diaphragm by disconnecting and observing the fuel pressure gage vent line while operating the appropriate electric fuel pump. If fuel is found in the vent line or flows from vent, replace gage. 2. Within the next 25 hours time in service after the effective date of this AD, install fuel float check valves, Aerostar Part Number A6601151, in accordance with instruction 11 of Aerostar Aircraft Corporation Service Bulletin No. 600-28, dated November 4, 1970, or later FAA approved revision. Alternate means of compliance or equivalent replacement parts may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. This amendment becomes effective to all known owners of Aerostar Model 600 and 601 airplanes upon receipt of individual copies mailed November 6, 1970, and to all other persons on November 16, 1970.
67-22-04: 67-22-04 BRITISH AIRCRAFT: Amdt 39-450 as amended by Amdt. Number 39-912. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated. To detect failures of joints in the secondary flap transmission shafts, accomplish the following: (a) On BAC 1-11 200 Series airplanes only, within the next 150 hours' time in service after the effective date of this AD, unless already accomplished, inspect all flap secondary transmission support bearing assemblies in accordance with British Aircraft Corporation (BAC) 1-11 Alert Service Bulletin No. 27-A-PM 1928, Issue 3, or later ARB-approved issue, or FAA- approved equivalent. All defective bearing assemblies must be replaced before further flight in accordance with this Service Bulletin, or FAA-approved equivalent. Non-defective bearing assemblies may be continued in service without further inspection. (b) On BAC 1-11 200 and 400 Series airplanes, within the next 150 hours' time in service after theeffective date of this AD, unless already accomplished within the last 450 hours' time in service and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, conduct a functional check of the flap secondary transmission system followed by a visual examination of the transmission shaft joints as detailed in British Aircraft Corporation Alert Service Bulletin No. 27-A-PM 1928, Issue 3, or later ARB-approved issue, of FAA- approved equivalent. Correct defects found before further flight. (c) The repetitive functional check and inspections required in paragraph (b) may be discontinued if the airplanes are modified in accordance with BAC Service Bulletin 27-PM-1928 paragraphs (a) and (b) and BAC Service Bulletin PM-2720 (a) and (b), or modified in accordance with BAC Service Bulletin PM-2720 (a), (b), (c), and (d), or FAA-approved equivalent. (d) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East 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 that operator. Amendment 39-450 effective August 19, 1967. This amendment (39-912) becomes effective January 11, 1970.
67-20-01: 67-20-01 ALLISON - AERO PRODUCTS: Amdt. No. 39-439 as revised Amdt. 39-466, Part 39, Federal Register June 29, 1967. Applies to Models A6441FN-606 and A6441FN-606A Propellers. Compliance required as indicated, unless already accomplished. To prevent serious overspeeds and to make the propeller pitch lock more effective under remote combinations of critical component failures, accomplish the following: (a) On or before November 1, 1967, install Part No. 6859637 restrictor in the increase pitch port of each hub island, as outlined in Allison Commercial Service Letter CSL 189, Pages 14 and 15, Paragraph C2b(1)(2)(3) and (4), entitled "Hub Assembly - Preparation for Assembly." (b) On or before November 1, 1967, remove the eight master gear retention bolts and install eight P/N 6859881 bolts as replacements, as outlined in Allison's Commercial Propeller Bulletin, CPB No. 63-317. This amendment effective August 23, 1967. Revised August 23, 1967.
91-04-08: 91-04-08 AEROSPATIALE: Amendment 39-6898. Docket No. 90-NM-226-AD. Applicability: Model ATR42-300 and ATR42-320 series airplanes, Serial Numbers 123 through 142, which have been fitted with Modification 1848 and have not incorporated Modification 2311, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of cockpit voice recorder (CVR) information, accomplish the following: A. Within 30 days after the effective date of this AD, restore the automatic shut-off feature to the CVR by rewiring relay 9RK, in accordance with Aerospatiale Service Bulletin ATR42-23-0018, dated July 13, 1989. B. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. 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 may obtain 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, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6898, AD 91-04-08) becomes effective on March 22, 1991.
76-06-10: 76-06-10 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2561. Applies to Model DH-104 "Dove" airplanes certificated in all categories which have not been modified in accordance with Dove Modification 1728. Compliance is required as indicated. To detect cracks in the nose landing gear inner casting, which could result in failure of the casing and collapse of the nose gear, accomplish the following: (a) For inner casings (P/N's 4UN.443ND and 4UN.555A) which have not been modified in accordance with either Dove Modification 847 or Modification 1008, comply with the following: (1) Locate and identify the inner casings in accordance with the instructions contained in paragraph 3.1 of Hawker Siddeley Aviation Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1973. (2) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter atintervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casing for cracks in accordance with paragraph 3.5 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1973, or an FAA approved equivalent. (3) If any cracks are found during an inspection required by paragraph (a)(2) of this AD, before further flight, except that the airplane may be flown in accordance with FAR's 21.197 and 21.199 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (a)(2) of this AD. Inspect the replacement casing for cracks in accordance with paragraph 3.5 of Hawker Siddeley Aviation Ltd., Technical News Sheet Series CT(104), No 232, Issue 1, dated September 17, 1973, or an FAA-approved equivalent, within the next 600 hours time in service from time of replacement and thereafter at intervals not to exceed 600 hours time in service from the last inspection. (b) For inner casings (P/N's 14UN.467A/ND and 14UN.469A/ND) which have been modified in accordance with either Modification 847 or Modification 1008, comply with the following: (1) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 600 hours time in service, and thereafter at intervals not to exceed 600 hours time in service from the last inspection, inspect the nose landing gear inner casings for cracks in accordance with paragraph 4.1 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1975, or an FAA approved equivalent. (2) If any cracks are found during an inspection required by paragraph (b)(1) of this AD, before further flight, except that the airplane may be flown in accordance with FAR's 21.197 and 21.199 to a base where the repair can be performed, replace the inner casing with a new part of the same part number or a serviceable used part of the same part number that has been inspected and found to be free of cracks in accordance with the inspection prescribed in paragraph (b)(1) of this AD. Inspect the replacement casing for cracks in accordance with paragraph 4.1 of Hawker Siddeley Aviation Ltd., Technical News Sheet, Series CT(104), No. 232, Issue 1, dated September 17, 1975, or an FAA approved equivalent, within the next 600 hours time in service from time of replacement and thereafter at intervals not to exceed 600 hours time in service from the last inspection. This amendment becomes effective on April 8, 1976.
77-15-10: 77-15-10 FILOTECNICA SALMOIRAGHI (AERITALIA S.p.A.): Amendment 39-2982. Applies to airspeed indicators, serial numbers 3800 and below, with part numbers - P/N 8.039.003 P/N 8.039.608.1 8.039.008 8.039.703 8.039.008.1 8.039.708 8.039.503 8.039.708.1 8.039.508 8.039.808 8.039.508.1 8.039.808.1 8.039.603 8.039.408 8.039.608 8.039.408.1 Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent the possibility of erroneous airspeed indications, accomplish the following: (a) Inspect the affected airspeed indicators for proper calibration by ensuring that the differential pressure values and tolerances for the indicator's airspeed range conform to those set forth in Tables I and II of SAE Aeronautical Standard AS-391B "Airspeed Indicator (Pitot Static)," dated December 15, 1954, or an FAA-approved equivalent. (b) If an airspeed indicator inspected in accordance with paragraph (a) of this AD is found not to be in proper calibration, scrap it. This amendment becomes effective August 4, 1977.
78-17-06: 78-17-06 PRATT & WHITNEY AIRCRAFT OF CANADA, LIMITED: Amendment 39-3286. Applies to all Pratt & Whitney Aircraft of Canada, Limited JT15D-4 engines prior to Serial Number PCE-70111 and Pratt & Whitney Aircraft JT15D-4 engines prior to Serial Number P-70111 with Part Number 3023031 and 3023035 fuel manifold adapter assemblies. Compliance required within the next 50 hours in service after the effective date of this AD, unless already accomplished. To preclude fuel leakage from the fuel adapter assemblies, replace the Part Number 3023031 and 3023035 fuel manifold adapter assemblies with Part Number 3021699 and 3021698 fuel manifold adapter assemblies in accordance with Paragraph 2, Accomplishment Instructions in Pratt & Whitney Aircraft of Canada, Limited Service Bulletin No. 7087 as revised or approved equivalent parts. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. All equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the Federal Aviation Administration (FAA). This amendment is effective August 31, 1978.
96-22-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4100 series airplanes, that requires replacement of the existing decompression panel on the aft bulkhead of the toilet compartment with a modified decompression panel. This amendment is prompted by a report that a decompression panel that does not meet flammability requirements was installed on these airplanes during manufacture. The actions specified by this AD are intended to prevent injury to the crew and passengers and damage to the airplane structure due to the incapability of the decompression panel to contain a fire.
92-10-02: 92-10-02 BRITISH AEROSPACE: Amendment 39-8235. Docket No. 91-NM-279-AD. Applicability: Model BAe 146-100A, -200A, and -300A series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of all radio communication, accomplish the following: (a) Within 60 days after the effective date of this AD, remove Capacitor C68 (2.2uF, 35V) from the central audio unit station selector boards in accordance with British Aerospace Modification Service Bulletin SB.23-36-01238A, dated December 21, 1990. (b) An alternative method 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, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with British Aerospace Modification Service Bulletin SB.23-36-01238A, dated December 21, 1990, certificated in any category. 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 British Aerospace, PLC. Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on June 11, 1992.
89-21-04 R1: 89-21-04 R1 BOEING: Amendment 39-6349 as corrected by Amendment 39-6549. Docket No. 88-NM-201-AD. \n\n\tApplicability: Model 767 series airplanes, equipped with Pratt and Whitney JT9D series engines or General Electric CF6-80A series engines, specified in Boeing Service Bulletin 767- 71-0041, dated September 22, 1988, certificated in any category.\n \n\tCompliance: Required within 15 months after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the potential for a thrust loss greater than the loss of one engine due to a lightning strike, accomplish the following: \n\n\tA.\tModify the engine electrical and electronic engine control wiring in accordance with Boeing Service Bulletin 767-71-0041, dated September 22, 1988; Revision 1, dated April 6, 1989; or Revision 2, dated June 29, 1989. \n\n\tB.\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\tC.\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, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThe effective date for the requirements of this amendment remains November 8, 1989, as specified in Amendment 39-6349, AD 89-21-04. \n\n\tThis AD revises AD 89-21-04, Amendment 39-6349. \n\tThis amendment (39-6549, AD 89-21-04 R1) becomes effective on March 29, 1990.
72-18-04: 72-18-04 HUGHES: Amendment 39-1509. Applies to Model 369H Series; Model 369HE, Serial Nos. 0101E thru 0215E, Model 369HM, Serial Nos. 0101M thru 0213M, Model 369HS, Serial Nos. 0101S thru 0357S Helicopters certified in all categories. Compliance required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To eliminate the possibility of exceeding the correct Vne limitations above 3000 feet density altitude, accomplish the following: (a) Install new Vne placards in accordance with Hughes Service Information Notice No. HN-45, dated 29 February 1972, or later FAA-approved revisions, or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. New placards are available from the Manufacturer and Service Centers. (b) Revise Rotorcraft Flight Manual with RFM revision dated 2 November 1971. RFM revisions are available from the Manufacturer and Service Centers. This amendment becomes effective August 31, 1972.
90-25-04: 90-25-04 McDONNELL DOUGLAS: Amendment 39-6817. Docket No. 90-NM-71-AD. \n\n\tApplicability: Models DC-9-81, -82, -83 and -87 (MD-81, -82, -83, and -87) series airplanes, and Model MD-88 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished since December 21, 1989. \n\n\tTo prevent the engine from departing the aircraft during a hard landing, in the event of a sudden engine seizure, or during flight when high velocity vertical gust is encountered, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, accomplish the following: \n\n\t\t1.\tPerform one of the following inspections: \n\n\t\t\ta.\tPerform a one-time visual inspection of both the left and right engine forward mount cone bolts for the correct part number, in accordance with McDonnell Douglas MD-80 Alert Service Bulletin A71-49, Revision 2, dated November 4, 1990 (from hereon referred to as the Service Bulletin). If the part number of the cone bolt is other than "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503, prior to further flight, remove and replace the bolt with a "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503 cone bolt; or \n\n\t\t\tb.\tPerform a one-time ultrasonic inspection of both the left and right engine forward mount cone bolts in accordance with the Service Bulletin. If the part shows an indication of shear section cut-out, remove and replace the bolt with a "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503 cone bolt. \n\n\t\t2.\tIncorporate a revision into the FAA-approved maintenance inspection program which provides for a visual or ultrasonic inspection of the engine forward mount cone bolts for "Barry" Part Number K2219-9SA3, or McDonnell Douglas Part Number 7938004-503, at each engine change and, if incorrect bolts are found, replace with "Barry" Part Number K2219-9SA3 or McDonnell Douglas Part Number 7938004-503 bolts before eachengine installation. \n\n\tB.\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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. \n\n\tC.\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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Business Unit Manager of Publications, C1-HCW (54-60). These documentsmay be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6817, AD 90-25-04) becomes effective January 2, 1991.