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71-11-01: 71-11-01 De HAVILLAND AIRCRAFT OF CANADA, LIMITED: Amdt. 39-1212. Applies to de Havilland Model DHC-6 Airplanes certificated in all categories.
Compliance required within the next 500 hours time in service after the effective date of this AD unless already accomplished.
To provide adequate protection for particular circuit wires, accomplish the following in accordance with the instructions contained in DHC Service Bulletin No. 6/245 dated October 9, 1970:
(a) Alter airplanes, S/Ns 6 through 289, except S/Ns 176, 221, 233, 268 and 286, by incorporating DHC Modification No. 6/1369;
(b) Alter airplanes, S/Ns 1 through 289, except S/Ns 176, 233, 268, and 286, by incorporating DHC Modification No. 6/1370;
(c) Alter airplanes, S/Ns 6 through 289, except S/Ns 176, 221, 233, 268 and 286, by incorporating DHC Modification No. 6/1371. Modification No. 6/1371 is applicable only to those airplanes in which DHC Modification No. 6/1053 has been incorporated;
(d) Alter airplanes, S/Ns 136 through 289, except S/Ns 176, 221, 233, 268, and 286, by incorporating DHC Modification No. 6/1372;
(e) Alter airplanes, S/Ns 136 through 289, by incorporating DHC Modification No. 6/1389.
Equivalent alterations may be used provided they are approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
This amendment is effective May 19, 1971.
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70-05-01: 70-05-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-945. Applies to Model BAC 1- 11 200 and 400 series airplanes.
To prevent false indication of a retracted flap position which could result in a failure of the flap structure in flight, within the next 1500 hours' time in service after the effective date of this AD, unless already accomplished, modify the flap signalling mechanism and flap control unit in accordance with British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 27-PM 3550, Revision 2, dated February 3, 1969, or later ARB-approved issue or an FAA-approved equivalent.
(British Aircraft Corporation Model BAC 1-11 Alert Service Bulletin No. 27-A-PM 3550, dated August 18, 1968, covers the same subject.)
This amendment becomes effective March 23, 1970.
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54-04-01: 54-04-01 AC SPARK PLUG: Applies to All Engines Equipped With AC LA-87 Spark Plugs, Except Pratt and Whitney R-1830 Engines of 1,200 HP or Less and Wright R-1820 Engines of 1,200 HP or Less.
Compliance required prior to March 1, 1954.
A. In order to preclude possibilities of engine failure, when using AC LS-87 spark plugs in engines for which they are not approved, these spark plugs must be removed from all engines with the exceptions of the R-1820 having a T.O. rating of 1,200 h.p. or less and the R-1830 having a T.O. rating of 1,200 h.p. or less.
B. On R-1820 and R-1830 engines of 1,200 h.p. or less, the LS-87 plug is limited to a maximum of 120 hours of service with no reconditioning permitted. Plugs having over 120 hours must be removed from service.
This supersedes AD 49-26-02.
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2016-03-02: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. ARRIEL 2C, 2C1, 2C2, 2S1, and 2S2 turboshaft engines with modification TU34 or TU34A installed. This AD requires inspecting the torque conformation box (TCB) for correct resistance values and removing TCBs that fail inspection before further flight. This AD was prompted by TCB failures. We are issuing this AD to prevent failure of the TCB, loss of engine thrust control, and damage to the helicopter.
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70-12-06: 70-12-06 NORTH AMERICAN ROCKWELL: Amdt. 39-1007. Applies to Models NA-265, NA-265-20, NA-265-30, NA-265-40 (Serial Nos. 282-1 through 282-97), and NA-265- 60 (Serial Nos. 306-1 through 306-63) airplanes.
Compliance required within the next 100 hours time in service after the effective date of this AD unless already accomplished.
To prevent severe nose gear shimmy and subsequent failure of the nose gear strut, modify the nose strut by the addition of a balance weight, support bracket and hardware, and replace five wheel brake system hydraulic lines located in the nose wheel well in accordance with the instructions contained in Los Angeles Division of North American Rockwell Corporation Sabreliner Field Service Bulletin No. 70-4, dated June 10, 1970, or later revision approved by the Chief, Aircraft Engineering Division, FAA Western Region.
This amendment supersedes Amendment 39-899 (34 F.R. 20418), AD 69-26-05.
This amendment becomes effective June 16, 1970.
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47-32-13: 47-32-13 BELL: (Was Mandatory Note 13 of AD-1H-1.) Applies to Models 47B and 47B3 Helicopters.
Compliance required at the next 100-hour teardown inspection.
Additional strength in the antitorque rotor control system has been found desirable as a result of service experience. This may be accomplished by replacing the aluminum alloy rivets in the tail rotor pitch adjustment rod assembly with steel rivets.
(Bell Service Bulletin 47C44 dated June 16, 1947, also covers this same subject.)
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2016-03-01: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of a crack of the forward leg of the left front spar lower chord and cracks on the lower wing skin at three fastener holes common to the nacelle outboard side load fitting. This AD requires repetitive inspections for cracks on the front spar lower chord, inspar skin, and wing skin, and corrective action if necessary. We are issuing this AD to detect and correct fatigue cracking of the forward leg of the front spar lower chord, inspar skin, and wing skin common to the nacelle outboard side load fitting, which could adversely affect the structural integrity of the wing.
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2016-01-10: We are superseding Airworthiness Directive (AD) 2004-20-14, for all Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes. AD 2004-20-14 required repetitive inspections to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 26 (left- and right-hand sides), and corrective actions if necessary. This new AD reduces the inspection compliance time and repetitive inspection intervals, and adds Airbus Model A300 C4-605R Variant F airplanes to the applicability. This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of cracks in the splice fitting at fuselage FR 47. We are issuing this AD to detect and correct cracking of the splice fitting at fuselage FR 47; such cracking could result in reduced structural integrity of the airplane.
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47-21-21: 47-21-21 REPUBLIC: (Was Service Note 1 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 to 236, Inclusive.
Inspection required immediately and periodically as noted below.
Inspect two slots at upper end of each tip float strut (P/N 17W23001) very carefully for cracks. Slots are located inside of wing contour, therefore, struts must be removed from wing at upper attachment for proper inspection. If any cracks are present, strut shall be replaced prior to further operation. All struts without relief holes at ends of slots as recommended by manufacturer shall be inspected for cracks at 50-hour intervals.
(Republic Seabee Service Bulletin No. 12 covers this same subject.)
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47-06-10: 47-06-10 CESSNA: (Was Mandatory Note 6 of AD-768-4.) Applies to 120 and 140 Aircraft Serial Numbers Up to and Including 9669.
Compliance required prior to April 1, 1947.
Install carry-through bar between the ends of the aileron control chain that is installed at the top of the control "T" to make a continuous loop at this chain installation so that both control wheels operate positively in the same direction. This is necessary to prevent possible locking of aileron system at full throw.
(Cessna Service Letter No. 17 dated September 19, 1946, covers this same subject.)
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