Results
2001-24-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F series airplanes. This AD requires an inspection of the power feeder cable assembly of the auxiliary power unit (APU) for chafing, correct type of clamps, and proper clamp installation; and corrective actions, if necessary. The actions specified by this AD are intended to prevent loss of the APU generator due to chafing of the generator power feeder cables, and consequent electrical arcing and smoke/fire in the APU compartment. This action is intended to address the identified unsafe condition.
2001-24-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4, A300 B4-600 and B4-600R, and A310 series airplanes, that requires modification of the terminal blocks of the starter feeder line of the auxiliary power unit (APU). This action is necessary to prevent slackness and subsequent overheat and arcing of certain wiring connections. This action is intended to address the identified unsafe condition.
92-21-02: 92-21-02 FOKKER: Amendment 39-8382. Docket No. 92-NM-107-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11262 through 11267, inclusive, and 11270 through 11376, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent an incorrect rudder deflection, accomplish the following: (a) Within 30 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) as follows. Paragraph (a)(1) of this AD may be accomplished by inserting a copy of this AD into the AFM. (1) Add the following to Section 2.04.01, SPEED LIMITATIONS: "MINIMUM V1 ON DRY OR WET RUNWAY IS 110 KNOTS. MINIMUM V1 ON ICY RUNWAY IS 117 KNOTS." (2) Amend Section 2.05.01, WEATHER LIMITATIONS, as follows: "MAXIMUM ALLOWABLE CROSS-WIND COMPONENT FOR TAKEOFF AND LANDING. . . . . . . . . . 25 KNOTS" (3) Amend Section 2.08.01, AFCAS LIMITATIONS, as follows: "DO NOT ENGAGE AP WHILE AFCAS IS IN TAKEOFF MODE. APPROACH/LANDING IN LAND MODE (GS/LOC IN FMA) DISENGAGE AP AT 1,500 FEET AGL AND CONTINUE APPROACH ON FLIGHT DIRECTOR." (b) Within 45 days after the effective date of this AD, inspect to determine the dimensions of the autopilot rudder servo input brackets of the rudder post assembly, part numbers 77938-003 and 77939- 003, in accordance with Fokker Service Bulletin SBF100-027-041, dated February 24, 1992. If brackets with incorrect dimensions are found, prior to further flight, replace those brackets in accordance with the service bulletin. (c) After accomplishment of paragraph (b) of this AD, the limitations required by paragraphs (a)(1), (a)(2), and (a)(3) of this AD may be removed from the FAA-approved Airplane Flight Manual. (d) 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 Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) 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. (f) The inspection and replacement shall be done in accordance with Fokker Service Bulletin SBF100-027-041, dated February 24, 1992. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (g) This amendment becomes effective on November 24, 1992.
2017-13-07: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD was prompted by a report that a main landing gear (MLG) door could not be closed due to rupture of the actuator fitting. This AD requires repetitive inspections for cracking of the MLG door actuator fitting and its components, and corrective actions if necessary. This AD also requires eventual replacement of all affected MLG door actuator fittings with new monoblock fittings, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
2001-24-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; and Model DC-9-81, -82, -83, and -87 series airplanes, that requires an inspection of the power feeder bus cables of the auxiliary power unit (APU) for overheat damage between certain fuselage stations; and corrective action(s), if necessary. This action is necessary to prevent loose terminal stud connections and consequent damage to the small copper terminals, which could result in overheating of the wires at the terminal strip. Such overheating could cause an electrical failure and could result in smoke and fire in the electrical/electronic compartment. This action is intended to address the identified unsafe condition.
2001-24-19: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; and Model MD-88 airplanes, that requires an inspection to detect chafing or overheat damage of the electrical wires located at fuselage station Y=110.000 bulkhead of the lower nose left tunnel; and corrective actions, if necessary. This AD also requires replacing the external power ground stud with a new ground stud using new attaching parts, torquing new attachments, and installing a nameplate. This action is necessary to prevent loose external power ground wires, which could cause arcing and overheated wire insulation and consequent smoke/fire in the cockpit. This action is intended to address the identified unsafe condition.\n\n\nDATES: Effective January 16 2002. The incorporation by reference of certain publications listed in the regulations is approved bythe Director of the Federal Register as of January 16, 2002.
52-01-06: 52-01-06 BELL: (Applies to All Model 47 series Helicopters Having Covered Tail Booms. Compliance required at next 300-hour overhaul, but not later than March 1, 1952. To prevent the main rotor striking the tail boom as a result of boom deflection when yawing at high forward speed, install the 47-706-211-1 or -2 spoiler on the tail boom. (Note: Spoiler must not be installed on any helicopter having an uncovered tail boom.) (Bell Service Bulletin No. 81 covers this same subject.)
2017-13-10: We are superseding Airworthiness Directive (AD) 2003-18-06, which applied to certain Airbus Model A319-131 and -132 airplanes; Model A320-231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. AD 2003-18-06 required installing new anti-swivel plates and weights on the engine fan cowl door (FCD) latches and a new cowl door hold-open device. This AD retains the previous actions and requires modifying the engine FCDs, installing placards, and re-identifying the FCDs. This AD also adds airplanes to the applicability. This AD was prompted by reports of additional engine FCD in-flight losses, and a new FCD front latch and keeper assembly that has been developed to address this unsafe condition. We are issuing this AD to address the unsafe condition on these products.
95-15-13: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action requires inspecting the main passenger/crew door locking mechanism to ensure that a taper pin is installed, installing a taper pin if not already installed, and modifying the passenger door warning system. The actions specified by this AD are intended to prevent the inability to open the passenger/crew door or failure of the passenger door warning system, which could result in passenger injury if emergency evacuation is needed.
77-14-18: 77-14-18 SIAI-MARCHETTI: Amendment 39-2968. Applies to F.260 and F.260B airplanes, Serial Numbers 101 thru 125, 2-26 thru 2-61, 3-76, 3-77, 3-78, 3-80, 3-84, 502, 10-09, and 20-01, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent structural failure and possible loss of airplane control due to fatigue cracks surrounding the control surface hinge bracket attachment holes, accomplish the following: (a) Comply with paragraph (c) of this AD in accordance with the following schedule: (1) For airplanes with 1000 or less hours time in service on the effective date of this AD, within the next 25 hours time in service unless accomplished within the past 475 hours time in service, and thereafter in accordance with subparagraph (3) of this paragraph. (2) For airplanes with more than 1000 hours time in service on the effective date of this AD, within the next 10 hours time in service, unless accomplished within the past 190 hours time in service, and thereafter in accordance with subparagraph (3) of this paragraph. (3) Continue to comply with paragraph (c) of this AD at intervals not to exceed 500 hours time in service until reaching 1000 hours total time in service and thereafter at intervals not to exceed 200 hours time in service. (b) The inspections required by paragraph (c) of this AD may be terminated - (1) With respect to individual affected areas upon compliance with paragraph (d) of this AD; or (2) Upon accomplishment of paragraph (e) of this AD. (c) Inspect the areas surrounding the control surfaces hinge bracket attachment holes for cracks using dye penetrant in accordance with - (1) SIAI Marchetti Mandatory Service Bulletins listed in paragraph (f) of this AD; (2) SIAI Marchetti Mandatory Service Bulletin S.B. No. 260B16 dated April 2, 1976; or (3) An FAA-approved equivalent of bulletins specified in paragraph (c)(1) and (c)(2) of this AD. (d) If a crack is found during the inspection required by paragraph (c) of this AD, before further flight, modify and repair the affected area in accordance with appropriate SIAI Marchetti Mandatory Service Bulletin listed in paragraph (f) of this AD, or an FAA-approved equivalent. (e) For areas where no cracks are found as a result of any inspection required by this AD, within the next 1,000 hours time in service after the effective date of this AD, perform the modifications and repairs specified in the SIAI Marchetti Mandatory Service Bulletins listed in paragraph (f) of this (AD), or FAA- approved equivalents. (f) The applicable areas and Service Bulletins are as follows: Affected Area Applicable Service Bulletin (1) Wing Rear Spar in the Flaps and Aileron Hinge Bracket Area S.B. 260B21 dated September 24, 1976. (2) Flaps Hinge Bracket Attachment Area S.B. 260B22 dated September 24, 1976. (3) Aileron Hinge Bracket Attachment Area S.B. 260B23 dated September 24, 1976. (4) Horizontal Stabilizer (Empennage) Rear Spar Hinge Bracket Attachment Area S.B. 260B24 dated September 24, 1976. (5) Rudder Spar Upper Hinge Bracket Attachment Area S.B. 260B25 dated September 24, 1976. (6) Elevator Outboard Hinge Bracket Attachment Area S.B. 260B26 dated September 24, 1976. (7) Horizontal Stabilizer Outboard Hinge Bracket Attachment Area S.B. 260B27 dated September 24, 1976. This amendment becomes effective July 28, 1977.
2001-24-24: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10 and -30 series airplanes, that requires an inspection of the power feeder cable for evidence of chafing, and repair of any chafed power feeder cable. This amendment also requires replacement of the wiring support clip (standoff) of the power feeder cable with a new, improved wiring support clip. This action is necessary to prevent chafing and arcing of the power feeder cable and adjacent airplane structure and system components, and consequent smoke/fire in an engine nacelle. This action is intended to address the identified unsafe condition.
2017-13-11: We are adopting a new airworthiness directive (AD) for all Model G-IV airplanes. This AD was prompted by a report indicating that the G-IV gust lock system allows more throttle travel than was intended and could allow the throttle to be advanced to reach take-off thrust. This AD requires modification of the gust lock system, and a revision of the maintenance or inspection program to incorporate functional tests. We are issuing this AD to address the unsafe condition on these products.
2010-26-04: We are adopting a new airworthiness directive (AD) for the products listed above that are equipped with Thielert Aircraft Engine GmbH (TAE) Engine Model TAE-125-01 installed per Supplemental Type Certificate (STC) No. SA03303AT. This AD requires installing a full authority digital engine control (FADEC) backup battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and revising the limitations section of the supplement airplane maintenance manual. This AD was prompted by an incident where an airplane experienced an in-flight engine shutdown caused by a momentary loss of electrical power to the FADEC. We are issuing this AD to prevent interruption of electrical power to the FADEC, which could result in an uncommanded engine shutdown. This failure could lead to a loss of engine power.
2001-24-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and -40 series airplanes and C-9 airplanes, that requires revising the wiring of the sidewall lights in the forward and aft passenger compartment. The actions specified by this AD are intended to prevent the control switch of the cabin sidewall lights on the forward attendant's panel from overheating, which could result in shorting of the dim, bright, and power terminals, and consequent smoke/fire in the passenger compartment. This action is intended to address the identified unsafe condition.
2017-13-01: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by a report of a crack in a certain body station (BS) frame inboard chord during supplemental structural inspection document (SSID) inspections. This AD requires repetitive detailed and high frequency eddy current (HFEC) inspections for any crack at the frame inboard chords, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
76-08-05: 76-08-05 DEHAVILLAND AIRCRAFT of CANADA, LTD: Amendment 39-2585. 1. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 15, 17, 22, 23, 26, 27 and 28, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/341. Compliance required within the next 100 hours in service after the effective date of this AD. To provide a more positive current return path from the fuel booster pump motor so as to eliminate the possibility of a fire hazard due to overheating of the pump, install cable jumper in accordance with "Modification Procedure" paragraph of DeHavilland Technical News Sheet, Series Otter, No. 22, or an approved equivalent alteration. --------------------------------------------------------------- 2. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 15, 17 thru 42, 44, 45, 46, 52 thru 65 and 67 thru 70, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/558.Compliance required within the next 100 hours in service after the effective date of this AD. To provide a greater margin of safety in the event of an engine compartment fire, replace breather pipe assembly part No. C3-E-3-5 and drain box part No. C3-L-11 with breather pipe assembly part No. C3-E-3-22 and drain box part No. C3-L-21 in accordance with paragraph "DATA" of DeHavilland Engineering Bulletin, Series "O", No. 5 or an approved equivalent alteration. --------------------------------------------------------------- 3. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 96 except 16, 77, 78, 79, 91, 93 and 94, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/680. Compliance required within the next 100 hours in service after the effective date of this AD. To prevent failure of the left hand upper exhaust pipe, part No. C3-EE-6/B, at a point immediately below the existing clamp bracket, install two additionalclamps part No. C3-EE-18 and support strut, part No. C3-EE-42, on exhaust pipes in accordance with paragraph 5. "PROCEDURE" of DeHavilland Engineering Bulletin, Series "O", No. 19, or an approved equivalent alteration. --------------------------------------------------------------- 4. Applies to all DHC-3 (U-1A) Airplanes prior to Serial Number 390 except Serial Number 320, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/865. Compliance required within the next 100 hours in service after the effective date of this AD. To reduce the possibility of in-flight failure of the oil delivery line from the Constant Speed Unit and resultant loss of engine oil, install an improved oil line assembly installation in accordance with paragraph "PROCEDURE" of DeHavilland Engineering Bulletin, Series "O", No. 68, Issue 3, or an approved equivalent alteration. --------------------------------------------------------------- 5. Appliesto all DHC-3 (U-1A) Airplanes prior to Serial Number 435, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/888. Compliance required at next engine removal but not later than the next 100 hours in service after the effective date of this AD. To provide fireproof integrity of the engine firewall, replace aluminum rivets with monel rivets and install sixteen additional steel bolts in accordance with paragraph "PROCEDURE" of DeHavilland Engineering Bulletin, Series "O", No. 72, or an approved equivalent alteration. --------------------------------------------------------------- 6. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 15 and 17, certificated in all categories. Compliance required as indicated: a. Within 50 hours in service after the effective date of this AD, unless already accomplished, inspect the fuselage former cap strips at Station 153.77 and 174.22 on left and right sides of the aircraft, in accordance with the procedure described in DeHavilland Aircraft, Ltd. Technical News Sheet, Series Otter No. 24, Modification Data, Part "A", or an approved equivalent inspection procedure. b. If additional rivets are determined necessary, after the inspection in paragraph (a) is completed, accomplish the installation in accordance with the above DeHavilland Modification Data, Part "B", or an approved equivalent alteration. --------------------------------------------------------------- 7. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 15, 17, 22, 23 and 25 thru 28, certification in all categories. Compliance required within the next 25 hours in service after the effective date of this AD, unless already accomplished. To ensure adequate locking of the rear cargo door, install straps, P/N C3-FF-351, or C3- FF-361-5 in accordance with the Modification Procedures and Sequence of Operation described in DeHavilland Aircraft, Ltd. Technical News Sheet, SeriesOtter No. 17, or install an approved equivalent alteration. --------------------------------------------------------------- 8. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 15, 17, 18, 20 thru 23, and 25 thru 31, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/349. Compliance required within the next 25 hours in service after the effective date of this AD. To prevent the cargo doors from being inadvertently opened, install handle guards, P/N C3-FS-524, on right and left side cargo door in accordance with paragraph "MODIFICATION DATA" of DeHavilland Aircraft, Ltd. Technical News Sheet, Series Otter, No. 21, or install an approved equivalent alteration --------------------------------------------------------------- 9. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 3 thru 17 except 16, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/193. Compliance required within the next 100 hours in service after the effective date of this AD. To stiffen skin panels around the access holes located in the rear of the fuselage, add required stiffeners in accordance with the "Modification Procedure" described in DeHavilland Aircraft of Canada, Ltd. Technical News Sheet, Series Otter, No. 9, or an approved equivalent alteration. --------------------------------------------------------------- 10. Applies to DHC-3 (U-1A) Airplanes with Serial Numbers 3 thru 15, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/149. Compliance required within the next 25 hours in service, unless already accomplished. To preclude the failure of existing attachments, replace 3/16 rivets with AN174-6 bolts for the attachment of the Rudder Quadrant Support Bracket, P/N C3-FS-169, in accordance with the "Modification Procedure" described in DeHavilland Aircraft, Ltd. Technical News Sheet, Series Otter No. 3, or an approved equivalent alteration. --------------------------------------------------------------- 11. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 15, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/203. Compliance required within 50 hours in service. To prevent rudder control reversal, install safety block, P/N C3-FS-504, for rudder pedal linkages, in accordance with the "Modification Procedure" described in DeHavilland Aircraft, Ltd. Technical News Sheet, Series Otter, No. 4, or an approved equivalent alteration. -------------------------------------------------------------- 12. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 208, except 135, 171, 176, 190, 193, 195, 197, 202 thru 204 and 207, certificated in all categories, but not altered in accordance with DeHavilland Modification 3/699. Compliance required within 100 hours in service after the effective date of this AD. Replace the present lower rudder hinge assembly, P/N C3-TR-14 in accordance with paragraph 6 "PROCEDURE" in DeHavilland Aircraft, Ltd. Engineering Bulletin, Series "O", No. 28, or an approved equivalent alteration. -------------------------------------------------------------- 13. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 177 except 16 and 67, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/670. Compliance required within 50 hours in service after the effective date of this AD. To prevent structural damage due to ground handling, reinforce the fuselage structure on left and right side, at the horizontal stabilizer attachment brackets, Station 427, in accordance with paragraph 6. "PROCEDURE" in DeHavilland Engineering Bulletin, Series "O", No. 29, or an approved equivalent alteration. --------------------------------------------------------------- 14. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 1 thru 300 and 324, certificated in all categories. Compliance required within the next 25 hours in service after the effective date of this AD, unless already accomplished. To prevent failure of the rudder control system, inspect Rudder Control Bellcrank Assemblies, P/Ns C3-CF-15 and CS-CF-15-7, for cracks using a dye penetrant method with a glass of at least 10 power, or using an approved equivalent inspection. For area of assemblies to be inspected refer to DeHavilland Aircraft of Canada, Ltd. Engineering Bulletin, Series "O", No. 63, Page 2, Figure 1. Replace cracked parts before further flight with parts of the same part number or approved equivalent parts. --------------------------------------------------------------- 15. Applies to all DHC-3 (U-1A) Airplanes operating on skis or wheel-skis, certificated in all categories. Compliance required, unless already accomplished, each time skis or wheel-skis are installed, or, within the next 50 hours in service, if the skis or wheel-skis arealready installed, and thereafter at intervals not to exceed 250 hours in service since the last inspection while operating on skis or wheel-skis. To detect cracks and preclude failures of the bolts attaching the upper end of the axle and compression struts to the fuselage, accomplish the following: a. Inspect in accordance with paragraph (1), (2) and (3) under the sub-title "Procedure" in DeHavilland Service Bulletin No. 3/12, Issue 2, or in accordance with an approved equivalent inspection. b. Replace cracked bolts, P/N C3U72-3 (axle strut) and P/N C3U142-5 with new bolts of the same part numbers, or approved equivalent bolts. c. If bolts are undamaged, reinstall and grease in accordance with DHC-3 Maintenance Manual Lubrication Instruction. --------------------------------------------------------------- 16. Applies to DHC-3 (U-1A) Amphibian Airplanes Serial Numbers 2 thru 410 only, certificated in all categories, but not altered in accordance with DeHavilland Modification 3/837. Compliance required within the next 100 hours in service after the effective date of this AD. In order to preclude damage due to landing on wheels, reinforce fuselage, forward and aft of joint, Station 264.00, in accordance with the "PROCEDURE" described in DeHavilland Aircraft, Ltd. Engineering Bulletin, Series "O", No. 57, Issue 2, or an approved equivalent alteration. --------------------------------------------------------------- 17. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 253, certificated in all categories. Compliance required within the next 25 hours in service after the effective date of this AD, unless already accomplished. Replace the two ESNA clinch nuts, P/N 22-NC6-048, holding the fork attachment fitting, P/N C3T15-5, to the tailplane with two ESNA clinch nuts, P/N 22- NC4-048, in accordance with paragraph 6. "PROCEDURE" in DeHavilland Aircraft of Canada, Ltd. Engineering Bulletin, Series "O", No. 47, Issue 2, orwith an approved equivalent alteration. --------------------------------------------------------------- 18. Applies to DHC-3 (U-1A) Airplanes, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/909. To prevent possible adverse airplane flutter effects from the flap interconnect tab on the elevator accomplish the following: 1. Compliance required within the next 50 hours in service after the effective date of this AD. a. Attach the following operating limitation placard near the airspeed indicator in full view of the pilot: "VNE SPEED SHALL NOT EXCEED 150 MPH (130 KNOTS) CAS." b. Conduct an inspection of the items listed in DeHavilland Aircraft of Canada, Ltd. Service Bulletin, Series Otter, No. 3/4, or an approved equivalent inspection. 2. Within three months after the effective date of this Airworthiness Directive accomplish either: a. An alteration of the red radial VNE line and the cautionary yellow arc of the airspeed indicator to reflect the VNE speed = 150 MPH (130 Knots) CAS, in accordance with an approved alteration; or b. A modification of the elevator tab horn in accordance with DeHavilland Aircraft of Canada, Ltd. Service Bulletin, Series Otter, No. 3/6, or an approved equivalent modification. 3. When either alteration in paragraph 2 of this AD item is incorporated the placard in paragraph 1(a) can be removed. --------------------------------------------------------------- 19. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 1 thru 356, certificated in all categories. 1. Compliance required within the next 50 hours in service, after the effective date of this AD, unless already accomplished. Perform the following in accordance with the "PROCEDURE" in DeHavilland Aircraft of Canada, Ltd. Engineering Bulletin, Series "O", No. 66, or an approved equivalent procedure. a. Visually inspect the wing strut spars P/N C3W101-4, on wing struts P/N C3W101-9, at both ends for cracks. b. If a crack is found at either end of the wing strut spar, which is less than 0.75 inch in length and does not enter a rivet hole, repair the spar prior to next flight, as in paragraph 3 of the above Bulletin, or an approved equivalent repair. c. If a crack is found longer than 0.75 inch in a strut spar, or a crack enters a rivet hole, prior to next flight, replace with a part of the same part number or an approved equivalent part, or repair in accordance with an approved procedure. --------------------------------------------------------------- 20. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 155, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/735. Compliance required within the next 100 hours in service after the effective date of this AD. To prevent inadvertent damage to the horizontal tail front hinge supporting structure, install "NO PUSH" signs on the leading edges of the left and right horizontal tail and elevator horns as indicated in paragraph 5 "PROCEDURE" of DeHavilland Aircraft of Canada, Ltd. Engineering Bulletin, Series "O", No. 32, or an approved equivalent alteration. --------------------------------------------------------------- 21. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 26, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/721. Compliance required at the next 50 hours in service after the effective date of this AD. To prevent damage to the horizontal tail front attachment brackets, accomplish the following: a. Reinforce the joint between the horizontal tail from attachment brackets, P/N C3-T5-15 and the horizontal tail structure by the installation of a pair of doubler plates on the horizontal tail lower surface skin in accordance with paragraph 6 "PROCEDURE " of DeHavilland Aircraft of Canada, Ltd. Engineering Bulletin, Series "O", No. 33, or an approved equivalent alteration procedure. b. Replace the existing 5/32 inch diameter dural rivets, P/N AN 456AD5 with 3/16 inch diameter steel bolts, P/N AN 173-6, for the attachment of the front attachment brackets to the horizontal tail, or approved equivalent parts. --------------------------------------------------------------- 22. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 192, except 176, 178, 181 and 190 certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/729. Compliance required within the next 50 hours in service after the effective date of this AD. To prevent the possible loss of the aileron center hinge bearing and to serve as a stop, install bolt, P/N C3-WF-54-3, in the outboard flap center hinge assembly in accordance with the "PROCEDURE" described in DeHavilland Engineering Bulletin, Series "O", No. 30, or with an approved equivalent alteration. -------------------------------------------------------------- 23. Applies to DHC-3 (U-1A) Airplanes, Serial Number 2 thru 126 except 67, 106, 114 and 120, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/711. Compliance required within the next 50 hours in service after the effective date of this AD. To prevent buckling or cracking in the nose flap center hinge ribs, reinforce the inboard nose flap center hinge rib in accordance with paragraph 6 "PROCEDURE" in DeHavilland Engineering Bulletin, Series "O", No. 24, or with an approved equivalent alteration. --------------------------------------------------------------- 24. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 270, 272, 275, 276 and 278, certificated in all categories and having steel bushings fitted to flap control rod sub assembly C3CF170-4, Mod. 3/288, but not altered in accordance with DeHavilland Modification No. 3/807. Compliance required within the next 25 hours in service after the effective date of this AD. To prevent the possible loss of the flap, replace the flap control rod sub assembly C3CF170-4 with C3CF170-11 in accordance with paragraph 6 "PROCEDURE" in DeHavilland Engineering Bulletin, Series "O", No. 49. --------------------------------------------------------------- 25. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 73 except Serial Numbers 16, 25, 27, 34, 43, 47 thru 51 and 67, certificated in all categories. Compliance required within the next 100 hours in service after the effective date of this AD, unless already accomplished. To provide adequate rivet connection of the top outer wing skin to the inner corrugated skin, inspect the top surface of the wing for excessive spacing between rivets, in accordance with paragraph 5 "PROCEDURE" in DeHavilland Engineering Bulletin, Series "O", No. 17 or an approved equivalent inspection. If excessive rivet spacing exists, install, before next flight, CR-163 4-2 Cherry rivet in accordance with the procedure in DeHavilland Engineering Bulletin, Series "O", No. 17, or with an approved equivalent alteration. --------------------------------------------------------------- 26. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 71 except 16, 25, 27, 34, 43, 47 thru 51 and 54, certificated in all categories, but not altered in accordance with DeHavilland Modification 3/458. To detect damage to the rudder control system, caused by heavy ground gust conditions on parked aircraft, accomplish the following visual inspection, after the effective date of this AD: a. Inspect, within the next 25 hours in service, unless already accomplished within the last 25 hours in service. b. Repeat this inspection at intervals thereafter not to exceed 100 hours in service. c. Inspect in accordance with paragraph 6 "DATA" in DeHavilland Aircraft, Ltd. Engineering Bulletin, Series Otter, No. 1, or an approved equivalent inspection. --------------------------------------------------------------- 27. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 54, certificated in all categories. Compliance required within the next 50 hours in service after the effective date of the AD, unless already accomplished. a. For rudder quadrant hub assemblies, P/N C3-CF-127, install six additional AN 456AD-4-14 rivets in accordance with paragraph 6. "DATA" in DeHavilland Engineering Bulletin, Series Otter, No. 3, or install an approved equivalent alteration. b. For elevator quadrant hub assemblies, P/N C3-CF-126, replace with P/N C3-CF-126-7, in accordance with paragraph 6. "DATA" in DeHavilland Engineering Bulletin, Series "O", No. 22, or an approved equivalent alteration. --------------------------------------------------------------- 28. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 1 thru 201, certificated in all categories, incorporating DeHavilland Modification No. 3/731, and P/N C3-CF-450-9 and -11, but not altered in accordance with DeHavilland Modification 3/772. Compliance required within the next 50 hours in service after the effective date of this AD. To prevent displacement of the wing flap actuating jack head assembly sintered metal filter, with consequent marginal engagement between the filter internal retainer and seal holder, remove sintered metal filter assembly from flap hydraulic jack, P/N C3-450-9 and -11 in accordance with paragraph 6. "PROCEDURE" in DeHavilland Aircraft of Canada, Ltd., Engineering Bulletin, Series "O", No. 38, or an approved equivalent alteration. -------------------------------------------------------------- 29. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 1 thru 40, certificated in all categories. Compliance required within the next 50 hours in service, unless already accomplished. To provide a more positive retainer for the piston tube of the main landing gear compression strut, P/N C3-U-104, alter the landing gear in accordance with "Modification Procedure" in DeHavilland of Canada, Ltd., Technical News Sheet, Series Otter, No. 23 including amendment No. 1, or an approved equivalent alteration. -------------------------------------------------------------- 30. Applies to DHC-3 (U-1A) Airplanes, Serial Number 1 thru 15 except 7, certificated in all categories without tail wheel steering, but not altered in accordance with DeHavilland Modification 3/132. Compliance required within the next 25 hours in service. To prevent possible loss of tail wheel assembly in flight, install P/Ns C3-UT-40, CW- UT-41, CW-UT-42, in accordance with "Modification Procedure" in DeHavilland Aircraft of Canada, Ltd., Technical News Sheet, Series Otter No. 6, or an approved equivalent alteration. --------------------------------------------------------------- 31. Applies to all DHC-3 (U-1A) Airplanes equipped with combination wheel-skis, certificated in all categories, but not altered in accordance with DeHavilland Modification 3/874. Compliance required at the next ski installation or within the next 50 hours in service after the effective date of this AD, whichever occurs first. To insure adequate lubrication of the main landing ski axle pin, install new axle pin P/N C3U5286-3 and bushing P/N C3U5287-3 in accordance with the "Modification Procedure" in DeHavilland Aircraft of Canada, Ltd., Engineering Bulletin, Series "O", No. 70, Issue 2, and its amendments 1 and 2, or an approved equivalent alteration. -------------------------------------------------------------- 32. Applies to DHC-3 (U-1A) Airplanes, Serial Numbers 2 thru 37 except 16 and 19, certificated in all categories, but not altered in accordance with DeHavilland Modification No. 3/374. Compliance required within the next 50 hours in service after the effective date of this AD. To provide a stronger and more positive attachment of the rear cabin seats to the luggage compartment post, install eyebolts P/N AN 43-17A, in accordance the "Modification Procedure" in DeHavilland of Canada, Ltd., Technical News Sheet, Series Otter, No. 25, or an approved equivalent alteration. --------------------------------------------------------------- Equivalent placards, signs, parts, inspection, procedures, instructions, repairs, alterations and modification, as applicable, must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Compliance with this Airworthiness Directive must be noted in the log book of the aircraft by referencing the Airworthiness Directive number and the specific item complied with; example: AD 76-08-05(2) if item 22 is being complied with. Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance times of this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective April 29, 1976.
2001-24-25: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, and - 40 series airplanes and C-9 airplanes. This amendment requires modification of the spoiler control system, and installation of protective interlock box assemblies in the spoiler circuit. This amendment is necessary to prevent smoke/fire in the flight compartment in the event that the automatic spoiler actuator overheats, and/or loss of the spoiler control system, which could significantly reduce the braking effectiveness of the airplane. This action is intended to address the identified unsafe condition.
85-07-05 R1: 85-07-05 R1 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39- 5028 as revised by Amendment 39-6354. Docket No. 89-NM-25-AD. Applicability: Model L-1011 series airplanes, Serial Numbers -1002 through -1221 that have not been modified in accordance with Lockheed Service Bulletin 093-21-184, dated November 21, 1983, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To minimize the potential for unrecoverable loss of all AC/DC electrical power, including the emergency bus, accomplish the following: A. Within 3,600 flight hours after May 9, 1985 (the effective date of Amendment 39- 5028), extend and reroute Fenwall thermal overheat sensors below the Mid-Electrical Service Center (MESC) floor, remove excess flow sensors, and modify the structure below the MESC floor in accordance with the Lockheed Service Bulletin 093-21-214, Revision 1, dated December 9, 1983; Revision 2, dated September 10, 1984; Revision 3, datedApril 21, 1986; or Part 1 of the Accomplishment Instructions of Revision 4, dated August 15, 1988. B. Within 3,600 flight hours after May 9, 1985 (the effective date of Amendment 39- 5028), extend the duct isolation barrier in accordance with Lockheed Service Bulletin 093-21-222, Basic Issue, dated January 9, 1984; Revision 1, dated April 30, 1984; or Revision 2, dated August 15, 1988. C. Within 3,600 flight hours after the effective date of this amendment, further extend the duct isolation barrier, add overheat sensors, and revise the insulation blanket retention, in accordance with Lockheed Service Bulletin 093-21-227, Basic Issue, dated August 15, 1988. D. 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, Los Angeles Aircraft Certification Office, 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, Los Angeles Aircraft Certification Office. E. 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 Lockheed Aeronautical Systems Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Department 65-33, Unit 20, Plant A-1. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This AD revises Amendment 39-5028, AD 85-07-05, which became effective on May 9, 1985. This amendment (39-6354, AD 85-07-05 R1) becomes effective on November 13, 1989.
75-15-03: 75-15-03 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2264: Applies to Model G-1159 airplanes, Serial Number 1 through 164 and 775. Compliance required as indicated: (1) Flight Manual. The emergency procedure set forth in Section A is effective upon receipt of this AD and must be incorporated in the Grumman Gulfstream II ARM, unless previously incorporated by Grumman Interim Revision 16-5 dated July 2, 1975. (2) Operating Limitation. The limitation set forth in Section B is effective upon receipt of this AD. It must be incorporated in the Grumman Gulfstream II AFM and remains effective until Grumman American Service Change 199 has been accomplished. (3) Replacement of stall barrier filters. Compliance with the filter change outlined in Section C is required within two hundred (200) flight hours, or three months, after the effective date of this AD, whichever occurs first. A. Emergency Procedures - Page 3-21 under Stall Barrier Malfunction, after item 5, add: If the stick pusher actuates in flight and cannot be deactivated using the above procedures, it is probable that a hydraulic malfunction has occurred in the stall barrier system. In this event, it will be necessary to continue the flight with the stall barrier actuated. The following procedures are recommended: 1. Cruise. With gear and flaps retracted, the airplane can be trimmed at airspeeds above approximately 200 knots. For maximum aircraft nose up trim, use the manual trim available beyond electric trim limit. The trim speed is reduced to a value below 200 knots when the flaps are extended. The trim tab deflection necessary for a trimmed condition will increase drag and reduce range by a small but undetermined amount. 2. Approach and Landing. a. The airplane CG may be adjusted as far aft as practicable, without exceeding the aft CG limit, by moving baggage and passengers rearward. b. Burn off fuel as required for a maximum landing gross weight of 46,000 pounds. c. With flaps 20 degrees, gear down, the airplane can be trimmed down to approximately 180 KIAS. d. On final approach at 170 KIAS, lower gear and landing flaps and reduce speed to 165 KIAS. This will result in a stick force of approximately 12 lbs. pull. Maintain 165 KIAS on final approach. The approach at 165 kts. and 39 degrees flaps will result in an attitude with the nose lower than normal. All other check list procedures are unchanged. e. At approximately 100 ft. above ground level slowly reduce the power to idle. The airplane should be flown onto the runway with a slight flare to assure that the nose wheel will not touch first. Plan to touch down at approximately 150 KIAS. Apply maximum reverse thrust and brake as necessary. Stick force during flare and touchdown will increase to about 30 lbs. Care should be taken not to flare high, thereby using more runway than necessary. f. Due to the higher touchdown speed, the landing distances will be increased. The required runway length has not been determined, but landings have been made in less than 7,000 feet of runway by using maximum reverse thrust and light braking. B. Limitations - Page 1-9. Under Stall Warning/Stall Barrier System add: INTENTIONAL STALLS ARE PROHIBITED. C. To prevent the stall barrier stick pusher from remaining energized after actuation, due to portions of the hydraulic filters becoming lodged in the stall barrier valves, accomplish the following: Replace the stall barrier hydraulic in-line filters and inspect and leak check the stall barrier valves and cylinder if the replaced filters are determined to be not intact upon removal, according to Grumman American Service Change 199, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region, Atlanta, Georgia. This amendment becomes effective July 18, 1975.
2022-21-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes), and A310 series airplanes. This AD was prompted by a determination that a new airworthiness limitation is necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate a new airworthiness limitation, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2017-13-02: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports that during the assembly of structural elements on some airplanes, lack of established procedures and tools caused boring and torqueing defects to be present at some locations. This AD requires a detailed visual inspection of bore holes for defects, replacement of bolts, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2025-11-09: The FAA is adopting a new airworthiness directive (AD) for certain Textron Aviation, Inc., Model 560 and 560XL airplanes. This AD was prompted by reports of mis-wired fire extinguishing bottles. This AD requires an engine fire extinguisher system functional test, an inspection of the fire extinguisher bottle cartridge wire numbers and yellow ID sleeves for proper identification and legibility, and applicable corrective actions. This AD also requires revising the existing inspection program to incorporate new airworthiness limitations for repetitive inspections of the engine fire extinguisher wiring and, as applicable, auxiliary power unit (APU) fire extinguisher wiring. The FAA is issuing this AD to address the unsafe condition on these products.
81-18-01 R1: This amendment revises an existing airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 helicopters that currently establishes a retirement life for the main rotor trunnion (trunnion) based on hours time-in-service (TIS). This amendment retains those requirements but revises the AD to remove the trunnion, part number (P/N) 206-011-120-103, from the applicability. This amendment is prompted by the issuance of another AD for the BHTI Model 206L and 206L-1 helicopters that requires a different method of calculating the retirement life for the trunnions. The actions specified by this AD are intended to prevent failure of the trunnion due to fatigue cracks and subsequent loss of control of the helicopter.
2023-02-08: The FAA is superseding Airworthiness Directive (AD) 2021-09- 13, which applied to certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes. AD 2021-09-13 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that additional new or more restrictive airworthiness limitations are necessary. This AD retains the requirement of AD 2021-09-13. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2025-11-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by an inspection that found several anodic burns on the main landing gear (MLG) bogie beam axles following a high velocity oxygen-fuel (HVOF) stripping process. This AD requires replacement of affected MLG bogie beam axles and prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.