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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.