Results
87-15-07: 87-15-07 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5643. Applies to Model 222, 222B, and 222U helicopters, certified in any category, with flapping bearing P/N 222-310-114-003/-105 installed. Compliance is required as indicated unless already accomplished. Compliance schedules required on page 1 of BHTI Alert Service Bulletins (ASB) Nos. 222-86-39, Rev. A and 222U-86-14, Rev. A are not required by this AD. To prevent failure of the M/R flapping bearing, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, perform Part I of the "Accomplishment Instructions" of BHTI ASB No. 222-86-39, Rev. A, dated January 14, 1987, for Model 222 and 222B helicopters and ASB No. 222U-86-14, Rev. A, dated January 14, 1987, for the Model 222U helicopter. If a crack is detected during the inspections, replace the M/R flapping bearing before further flight. (b) Within the next 100 hours time in service after the effective date of this AD, perform Part II of the "Accomplishment Instructions" of BHTI ASB No. 222-86-39, Rev. A, dated January 14, 1987, for the Model 222 and 222B helicopters and ASB No. 222U-86-14, Rev. A, dated January 14, 1987, for the Model 222U helicopters. (c) Comply with Part III of the "Accomplishment Instructions" of BHTI ASB No. 222-86-39, Rev. A, dated January 14, 1987, for the Model 222 and 222B helicopters and ASB No. 222U-86-14, Rev. A, dated January 14, 1987, for the Model 222U helicopter on the effective date of this AD. (d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Helicopter Certification Branch, Southwest Region, Department of Transportation, Federal Aviation Administration, Fort Worth, Texas 76193-0170. The above procedures shall be done in accordance with BHTI ASB Nos. 222-86-39, Rev. A, dated January 14, 1987, or 222U-86-14, Rev. A, dated January 14,1987, as appropriate. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) (1) and 1 CFR Part 51. Copies may be obtained from BHTI, P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment, 39-5643 becomes effective on August 7, 1987.
2020-05-11: The FAA is adopting a new airworthiness directive (AD) for Robinson Helicopter Company Model R44 and R44 II helicopters with an agricultural spray system installed by Supplemental Type Certificate (STC) SR00286BO (spray system). This spray system is also known as a Simplex Manufacturing Company (Simplex) Model 244 spray system. This AD was prompted by a report of an in-flight failure of the spray system elbow pump fitting (pump fitting). This AD requires repetitive inspections of the spray system pump fitting, corrective action if necessary, replacement of the spray system pump fitting, and installation of hose supports and a pump outlet cover. The FAA is issuing this AD to address the unsafe condition on these products.
78-23-09: 78-23-09 PIPER: Amendment 39-3342. Applies to Piper Model PA-38-112 Serial Nos. 38-78A0001, 38-78A0004 thru 38-78A0016, 38-78A0018 thru 38-78A0040, 38-78A0042 thru 38-78A0224, 38-78A0226 thru 38-78A0232, 38-78A0234 thru 38-78A0236, 38-78A0238 thru 38-78A0250, 38-78A0252 thru 38-78A0266, 38-78A0268, 38-78A0270 thru 38-78A0273, 38-78A0276, 38-78A0277, 38-78A0279 thru 38-78A0284, 38-78A0286 thru 38-78A0289, 38-78A0291, 38-78A0298, 38-78A0315 thru 38-78A0318, 38-78A0324, 38-78A0326, 38-78A0329 certificated in all categories. To prevent possible separation of the control wheel from the control shaft, accomplish the following: Before further flight, unless already accomplished, inspect and alter or replace the pilot and co-pilot control wheels in accordance with the "Instructions" section of Piper Service Bulletin No. 609 dated June 17, 1978, or equivalent which must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. This amendment is effective November 13, 1978.
81-19-01: 81-19-01 BELL HELICOPTER TEXTRON (BHT): Amendment 39-4207. Applies to Model 212 series helicopters certificated in all categories (Airworthiness Docket No. 81-ASW- 38). To prevent possible failure of main rotor yoke Part Number 204-011-102 (all dash numbers), accomplish the following: a. Unless Bell Helicopter Textron Alert Service Bulletin No. 212-81-23 has been previously complied with, within 10 days after the effective date of this Airworthiness Directive: (1) Create a component history card for yoke Part Number 204-011-102 (all dash numbers). (2) Record the operating time accumulated on the yoke as follows: a. For each flight hour of passenger or internal cargo operation, enter 1 hour on the component history card. b. For each flight hour involving external load operations where more than four lifts per hour occur, including those conducted under Federal Aviation Regulation Parts 133 and 137, enter 5 hours on the component history card.c. If operating time for the yoke is unknown, enter 2,400 hours on the component history card. (3) Yokes with more than 3,300 hours time on the compliance date of this AD must be retired prior to obtaining an additional 300 hours time. (4) Yokes with less than 3,300 hours time on the compliance date of this AD must be retired on or before attaining 3,600 recorded hours. b. The 3,600-hour life and the above method of recording flight hours on the yoke component history card shall continue in effect on all Part Number 204-011-102 yokes. c. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. d. In accordance with FAR 21.197 flight is permitted to a base where the requirements of this AD may be accomplished. This amendment becomes effective September 30, 1981.
64-16-03: 64-16-03 FAIRCHILD: Amdt. 771 Part 507 Federal Register July 23, 1964. Applies to Model F-27 Series Aircraft. Compliance required within 300 hours' time in service after the effective date of this AD, unless already accomplished. Rebalance the rudder in accordance with the procedures specified in Section 2, "Accomplishment Instructions", of Fairchild Service Bulletin 27-38, or an equivalent approved by the Engineering and Manufacturing Branch, FAA Eastern Region. (Fairchild Service Bulletin 27-38 dated May 4, 1964, covers this same subject.) This directive effective July 23, 1964.
80-15-04: 80-15-04 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-3842. Applies to Falcon 10 airplanes, Serial Numbers 1 through 122 except 118 and 121, 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 prevent inadvertent unlocking of the passenger door in flight, accomplish the following: (a) Modify the passenger door control mechanism by installing a microswitch connected to a cockpit annunciator "CABIN" light and install a transparent cup around the passengers' door control mechanism unlocking pushbutton in accordance with Avions Marcel Dassault (AMD) Service Bulletin AMD-BA F10-0163 dated May 17, 1978, and Revision 1 dated June 9, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (b) Revise the airplane maintenance manual and illustrated parts catalog for modifications performed in complying with paragraph (a) of this AD. This amendment becomes effective August 11, 1980.
2008-04-06: We are adopting a new airworthiness directive (AD) for all Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD requires repetitive inspections for any cracking of or damage to the left side and right side flight deck No. 2, No. 4, and No. 5 windows, as necessary, and corrective actions if necessary. This AD results from reports of in-flight departure and separation of the flight deck windows. We are issuing this AD to detect and correct cracking in the vinyl interlayer or damage to the structural inner glass panes of the flight deck No. 2, No. 4, and No. 5 windows, which could result in loss of a window and rapid loss of cabin pressure. Loss of cabin pressure could cause crew communication difficulties or crew incapacitation.
78-08-03: 78-08-03 PIPER: Amendment 39-3178 as amended by Amendment 39-3339. Applies to Piper Models PA-23 and PA-23-160, Serial Nos. 23-1 and up certificated in all categories. To prevent hazards in flight associated with cracks in the rudder upper hinge reinforcing bracket or rudder lower hinge bracket assembly, accomplish the following: (a) Within the next 25 hours in service from the effective date of this AD or upon the attainment of 1000 total hours in service, whichever is later, remove the rudder upper hinge P/N 17063-03 and inspect the rudder upper hinge reinforcement bracket P/N 17067-18 or equivalent for cracks using a dyne penetrant or equivalent method. Also inspect the rudder lower hinge bracket assembly P/N 17289-00 in the bearing area for cracks using a dye penetrant or equivalent method. (b) Within 1000 hours in service after the inspection in (a), and thereafter at intervals not to exceed 1000 hours since the last inspection accomplish the inspections required in (a). (c) If cracks are found in the reinforcing bracket during the inspections of paragraphs (a) or (b) remove it and inspect the spar web for cracks using a dye penetrant method or equivalent. (d) Cracked parts must be replaced using undamaged parts of the same part number or equivalent before further flight. (e) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region or accomplished in accordance with Advisory Circular 43.13-1A and approved by an FAA Maintenance Inspector. (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 intervals specified in this AD. (g) Report positive findings from paragraph (a) to Chief, Engineering and Manufacturing Section, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-R0174). Amendment 39-3178 was effective April 14, 1978. This amendment 39-3339 is effective November 10, 1978.
88-20-01: 88-20-01 BEECH: Amendment 39-6017. Applies to the following airplanes certificated in any category: MODEL SERIAL NUMBER F33A CE-1162 through CE-1223 A36 E-2383 through E-2405 E-2407 through E-2409 B36TC EA-468 through EA-470 EA-472 through EA-474 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent a potential fire in the cabin, accomplish the following: (a) Remove the Mortell 931 sound deadener material from the aft side of the firewall in accordance with the instructions in Beech Service Bulletin Number 2249, dated April 1988. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; Telephone(316) 946-4400. All persons affected by this directive may obtain copies of this document referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine this document at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6017, becomes effective on October 19, 1988.
2020-05-10: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of an incorrect version of EASy ''Top-Level System'' operational software installed in the avionics system due to use of an improper CD-ROM. This AD requires ensuring that the correct versions of the operational software and CD-ROM are installed, and doing corrective action if necessary, 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.