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98-17-07: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0070 and Mark 0100 series airplanes, that requires inspection of the wing leading edge sections for the correct amount of bleed air exhaust holes, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent malfunction of the wing leading edge thermal anti-ice system, which could result in reduced controllability of the airplane and/or reduced structural integrity of the wing due to overheating.
2020-07-14: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer indicating that the existing bond path design provides insufficient bond resistance margin between the fuel pump motor/impeller and structure. This AD requires replacement of the bonding jumpers on the auxiliary power unit (APU) fuel pump. This AD also requires, for certain airplanes, installation of a second bonding jumper; an inspection of the override/jettison fuel pumps and transfer/ jettison fuel pumps to determine if the bonding jumper has a one-piece braid or two-piece braid and replacement of the bonding jumper if necessary; and replacement of the bonding jumper on the electrical scavenge fuel pump. The FAA is issuing this AD to address the unsafe condition on these products.
81-10-01: 81-10-01 PIPER AIRCRAFT CORPORATION: Amendment 39-4095. Model PA-44-180 (Seminole), serial numbers 44-7995001 through 44-8095021, airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent cracks in the nose cone spars which could result in malfunction of the nose landing gear, accomplish the following: a. Within the next 50 hours time in service after the effective date of this AD, visually inspect the nose cone spars for cracks, in accordance with the instructions contained in Part I of Piper Aircraft Corporation Service Bulletin No. 695, dated September 10, 1980. If cracks are found, either modify as described in paragraph b below, or replace parts as required by Part I of the Piper Service Bulletin. The required inspection must be accomplished by a person authorized in accordance with FAR Part 43. b. Within the next 100 hours time in service after the effective date of this AD, modify the nose conespars in accordance with Piper Kit P/N 764 080V unless already accomplished. c. Make appropriate maintenance record entry. An equivalent method of compliance may be accomplished if approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment becomes effective April 30, 1981.
96-18-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires visual inspections to detect cracks of the fittings of the pressurized floor at frame 36, and renewal of the zone protective finish or replacement of fittings with new fittings, if necessary. This amendment is prompted by a report of fatigue cracking found on the pressurized floor fitting at frame 36 under the lower surface panel. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in failure of a floor fitting and subsequent depressurization of the fuselage.
77-17-01: 77-17-01 CANADAIR: Amendment 39-3007. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories, that have not been altered in accordance with Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an FAA- approved equivalent alteration. Compliance required as indicated. (a) To ensure the structural integrity and prevent failure of the following nose landing gear upper radius rods, accomplish the inspection in (1). Upper Radius Rod Subassembly Upper Radius Rod Item 1. 44-85045 LH Assembly Employs 44-85084 LH Rod Item 2. 44-85045-1 RH " " 44-85084-1 RH Rod Item 3. 44-85045-1000 LH " " 44-85084-2 LH Rod (1) For parts which have accumulated 1175 or more landings on the effective date of this airworthiness directive, inspect Items 1, 2, and 3 within the next 75 landings by a dye penetrant, eddy current, or ultrasonic method in accordance with the "Inspection Data" and "Inspection Procedure" sections of Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an FAA-approved equivalent inspection. (2) For parts which have not accumulated 1175 landings on the effective date of this airworthiness directive, accomplish the inspection in (a)(1) before attaining 1250 landings. (b) Repeat inspections in (a)(1) at intervals not to exceed: (1) 60 landings for non-reworked parts Item 1 and 3 (2) 200 landings for non-reworked part Item 2 (3) 30 landings for reworked parts Item 1, 2, and 3 (c) Replace cracked parts with new parts of the same part number or with approved equivalent parts, or rework cracked parts to the limitations specified in "Rework Instruction" in Canadair Service Information Circular No. 151-CL44, Issue 3, dated October 26, 1976, or with an approved equivalent procedure. (d) Replace parts reworked to the maximum limits, specified in "Rework Instruction" in theabove Service Information Circular, that have attained an additional 3000 landings from the time of such rework, or when cracks are again detected, whichever occurs first, with new parts of the same part number or with approved equivalent parts. (e) Equivalent inspections/procedures and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (f) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection times specified in this AD. This amendment is effective August 18, 1977.
2020-07-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that during ALTS CAP or (V) ALTS CAP mode, the flight guidance/autopilot does not account for engine failure while capturing an altitude. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with new warnings for ''Autoflight'' and ''Engine Failure in Climb During ALTS CAP.'' The FAA is issuing this AD to address the unsafe condition on these products.
78-05-04: 78-05-04 MCDONNELL DOUGLAS: Amendment 39-3150. Applies to DC-10-10, -10F, -30, -30F and -40 series airplanes, certificated in all categories. \n\n\tCompliance required within 30 days after the effective date of this AD, unless already accomplished. \n\n\ta.\tTo prevent a total Automatic Landing System disengagement below the alert height during a Category III approach because of a single failure, accomplish the following: \n\n\tIncorporate the following revision in the applicable Flight Guidance Appendices IV, IVA and etc., of the FAA Approved Airplane Flight Manual documents MDC-J1010, MDC-J1030, MDC-J5830, MDC-J1040 and MDC-J2140: \n\n\tAdd the following as the last entry in Section I Limitations: \n\n\t\t"Category III Automatic Landing \n\n\t\tIn addition to the Automatic Landing System Limitations listed above, the following limitation \t\tapplies: \n\n\t\tDo not use automatic landing system for Category III operation unless DC-10 Service Bulletin \t\t34-84 or production equivalent is incorporated." \n\n\tb.\tEquivalent modifications, procedures, or revisions may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective April 8, 1978.
80-20-05: 80-20-05 PIPER AIRCRAFT CORPORATION: Amendment 39-3926. Applies to the following PA-32RT-300T model serial numbers, certificated in all categories: \n\n\n32R-7887001 through 32R-7887222, \n32R-7887224 through 32R-7887226, \n32R-7887228 through 32R-7887237, \n32R-7887239 through 32R-7887243, \n32R-7887246 through 32R-7887254, \n32R-7887256 through 32R-7887261, \n32R-7887263, 32R-7887265 through 32R-7887289, \n32R-7987001, 32R-7987002 and 32R-7987004 through 32R-7987011, \n32R-7987013, 32R-7987014 and 32R-7987016 through 32R-7987020, \n32R-7987024, 32R-7987028 through 32R-7987030, \n32R-7987032, 32R-7987034, 32R-7987035, 32R-7987038, 32R-7987039, \n32R-7987041, 32R-7987042, 32R-7987044 and 32R-7987046, \n32R-7987049 through 32R-7987051, \n32R-7987054 through 32R-7987058, \n32R-7987060, 32R-7987066 and 32R-7987068 through 32R-7987070, \n32R-7987072 through 32R-7987073, 32R-7987075, 32R-7987076 and 32R-7987078 through 32R-7987080, \n32R-7987082 through 32R-7987086, \n32R-7987088, 32R-7987089, 32R-7987091, 32R-7987094, \n32R-7987096 through 32R-7987099, \n32R-7987101, 32R-7987102, 32R-7987104, \n32R-7987107 through 32R-7987115, \n32R-7987117 through 32R-7987119,\n32R-7987123 \n\n\tNOTE: The requirements of emergency airworthiness directive issued June 14, 1979, were found to be not applicable to the following serial numbers: \n\n\n32R-7887223, 32R-7887227, 32R-7887238, 32R-7887244, \n32R-7887245, 32R-7887255, 32R-7887262, 32R-7887264, \n32R-7987003, 32R-7987012, 32R-7987015, 32R-7987021, \n32R-7987022, 32R-7987023, 32R-7987025, 32R-7987026, \n32R-7987027, 32R-7987031, 32R-7987033, 32R-7987036, \n32R-7987037, 32R-7987040, 32R-7987043, 32R-7987045, \n32R-7987047, 32R-7987048, 32R-7987052, 32R-7987053, \n32R-7987059, 32R-7987061, 32R-7987062, 32R-7987063, \n32R-7987064, 32R-7987065, 32R-7987071, 32R-7987074, \n32R-7987077, 32R-7987081, 32R-7987087, 32R-7987090, \n32R-7987092, 32R-7987093, 32R-7987095, 32R-7987100, \n32R-7987103, 32R-7987105, 32R-7987106, 32R-7987116,32R-7987120, 32R-7987121, 32R-7987122, 32R-7987124, \n32R-7987125, 32R-7987126. \n\n\tCompliance is required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent a possible turbocharger exhaust coupling failure, which could result in a fire hazard, accomplish the following: \n\n\t(a)\tGain access to turbocharger exhaust system. \n\n\t(b)\tRemove the turbocharger exhaust coupling P/N 556 108 and tailpipe P/N 98705- 2. \n\n\t(c)\tUsing either a dye penetrant method or a 10-power magnifying glass, inspect coupling, coupling bolt, tailpipe and tailpipe flange for cracks, deformation or damage. \n\n\t(d)\tMeasure width across inside opening of retainer segments of coupling. Maximum allowable dimension is .350 in (See Figure 1) \n\n\t(e)\tMeasure thickness of tailpipe flange at apex. Dimension required is .096 plus or minus .005 inch. (See Figure 1) \n\n\t(f)\tIf flange dimension is under the tolerance shown in (e) above, replace tailpipe. If over tolerance, rework the flange mating surface to dimensions in (e) above, provided .005 inch flatness is maintained or replace with serviceable part. \n\n\t(g)\tReplace any exhaust system parts found cracked, deformed or damaged during the inspection required above with a serviceable part, before further flight. \n\n\t(h)\tReinstall serviceable parts as follows: \n\n\t\t(1)\tAssure turbocharger and tailpipe flange are properly aligned. Tap coupling gently to distribute band tension while tightening coupling nut. \n\n\t\t(2)\tTorque coupling nut to 40-50 inch pounds and safety wire. \n\n\t(i)\tMake appropriate maintenance record entry. \n\n\tAn equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. \n\n\tThis amendment is effective upon publication in the Federal Register as to all persons, except those persons to whom it was made immediately effectiveby priority mail, issued June 14, 1979, which contained this amendment. \n\n\n\n\nFIGURE 1 \nAD 80-20-05
99-07-13: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes. This amendment requires a one-time visual inspection to detect relative movement or deformation of the joint areas of the rear attaching supports and lower skin of the left and right outer flaps; repetitive borescopic inspections to detect cracking of the spar and of the rear internal support fittings of the outer flaps; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the rear internal support fittings of the outer flap structure, which could result in failure of the outer flaps, and consequent reduced controllability of the airplane.
77-11-03: 77-11-03 BEECH: Amendment 39-2913. Applies to Model 278 propellers installed on Models H35, J35, K35, M35, N35, P35, A45 (T34A), B45 and D45 (T34B) airplanes. Compliance: Required as indicated, unless previously accomplished. To prevent loss of propeller control, accomplish the following: A) Within 100 hours' time in service after the last inspection accomplished per AD 69-26-04, using dye penetrant procedures, inspect Beech P/N 278-336 pitch control bolts for evidence of cracks in the exposed thread runout area between the hex flats and the aft pitch setting nut. If a crack is detected, install Beech Kit No. 278- 0002S incorporating Beech P/N 278-368-1 or -3 pitch control bolts and steel pitch control yoke, in accordance with Beechcraft Service Instructions 0302-248, or later approved revisions. B) Within 100 hours' time in service after the effective date of this AD, install Beech Kit No. 278- 0002S incorporating P/N 278-368-1 or -3 pitch control bolts and steel pitchcontrol yoke, in accordance with Beechcraft Service Instructions 0302-248, or later approved revisions. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This AD supersedes AD 69-26-04 (Amendments 39-897 and 39-967). This amendment becomes effective July 16, 1977.