Results
71-02-05: 71-02-05 AEROSTAR: Amdt. 39-1147. Applies to Model 600 and 601 airplanes, Serial Numbers 60-0001 through 60-0056 and 61-0001 through 61-0070. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible separation of the main cabin door from the airframe, inspect the cabin door lock pins, replace any missing washers, adjust pins and torque lock nut in accordance with the Instructions in Aerostar Service Letter #600-19 dated 22 September 1970 or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA, Fort Worth, Texas. This amendment becomes effective January 23, 1971.
67-31-06: 67-31-06 FAIRCHILD-HILLER: Amdt. 39-517 Part 39 Federal Register December 1, 1967. Applies to Fairchild Hiller Aircraft FH-227. Compliance required as indicated. Within the next five hours' time in service unless already accomplished. Visually inspect the three elevator trim tab hinges for elongated holes in the clevis holes of the aluminum blocks located behind the three elevator trim tab hinges. Also, visually inspect each elevator trim tab hinge bearing for damage. Remove and replace blocks containing elongated holes and damaged bearings with an unused part of the same part number. Remove and replace trim tab clevis hinge containing a damaged block or bearing. This amendment effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated November 9, 1967.
2010-01-07: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: * * * * * * * * Revision 00 of AIRBUS A340 ALS [Airworthiness Limitations Section] Part 3: --adds new CMR (Certification Maintenance Requirements) tasks associated with modifications, --revises the applicability of some CMR tasks, --revises some CMR tasks with increased intervals, --revises a CMR task with a more restrictive interval, --deletes CMR task 282300-B0002-1-C * * *. Some of those changes constitute more restrictive requirements for aeroplane configuration already in service. Failure to comply with this Revision 00 of AIRBUS A340 ALS Part 3 constitutes an unsafe condition. * * * * * The unsafe condition is a safety-significantlatent failures that would, in combination with one or more other specific failures or events, result in a hazardous or catastrophic failure condition. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
79-13-02: 79-13-02 RAISBECK: Amendment 39-3499 as amended by amendment 39-3539. Applies to Rockwell Model NA 265-60 airplanes equipped with the Raisbeck Mark Five modification in accordance with STC SA687NW. A. To prevent possible jamming of the aileron system, before further flight, unless already accomplished, complete the following: 1. Deactivate the flap system by pulling and collaring the circuit breaker which supplies power to the flap motor. 2. Install a placard in full view of the flight crew which reads "FLAP SYSTEM INOPERATIVE." B. The following operating limitations apply: 1. Landing operations at or above VFR minimums only. 2. Conduct takeoffs in accordance with the Airplane Flight Manual. 3. Add 50 percent to factored landing distance (FAR 121). 4. For landings on wet runways, increase dry runway distance as determined per item 3 by a factor of 15 percent. Thrust reversers must be used. C. Amendment 39-3499 was effective July 1,1979, and was effective earlier for all recipients of the telegram as amended. D. Installation of the modifications in accordance with FAA-approved Raisbeck Mark Five Sabreliner Service Bulletin No. 5 (or equivalent modifications approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region) and incorporation of Change I of the FAA-approved Airplane Flight Manual (Raisbeck Report 76-601 for S/N 306-64 and subsequent; and 76-602 for S/Nos. 306-1 through 306-63), constitute terminating action to the requirements of this Airworthiness Directive. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to The Raisbeck Group, 7777 Perimeter Road South, Boeing Field International, Seattle, Washington 98108. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment 39-3539 becomes effective September 4, 1979.
89-26-05: 89-26-05 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6421. Docket No. 89-NM-175-AD. Applicability: De Havilland Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent possible collapse of a main landing gear (MLG) due to failure of the MLG upper lock strut, accomplish the following: A. Within 50 hours time-in-service after the effective date of this AD, inspect the left and right main MLG upper lock struts to determine the part number of the struts. Accomplish this inspection in accordance with de Havilland Alert Service Bulletin A7-32-93, dated January 30, 1989. B. If the part number is identified to be either 15707-5 or 15707-7 (subassembly P/N 15709-7 or 15709-9), the airplane may be returned to service after reprotecting the part with alodine solution number 1200 and grey epoxy paint. C. If the part number is 15707-3, or is both 15707-3 and 15707-5, or cannot be positively identified, prior to further flight, perform a one-time NDT inspection for cracks, in accordance with de Havilland Service Bulletin No. 7-32-21, Revision B, dated October 1, 1982; and thereafter perform a visual inspection for cracks prior to the first flight of each day. Upper lock struts with cracks must be replaced prior to further flight. D. Replacement with a P/N 15709-7 or 15709-9 upper lock strut subassembly (machined P/N 15707-5 or 15707-7), constitutes terminating action for the repetitive inspections required by paragraph C., above. E. Within 90 days after the effective date of this AD, replace upper lock struts having part number 15707-3, or both 15707-3 and 15707-5, or those that cannot be positively identified, with P/N 15709-7 or 15709-9 upper lock strut subassembly (machined P/N 15707-5 or 15707-7). This constitutes terminating action for the repetitive inspection requirements of this AD. F. 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, New York Aircraft Certification Office, FAA, New England 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, New York Aircraft Certification Office. G. 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 Boeing Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. This AD supersedes AD 80-17-13, Amendment 39-3885. This amendment (39-6421, AD 89-26-05) becomes effective on January 14, 1990.
2010-01-01: The FAA is superseding an existing airworthiness directive (AD), which applies to all Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F series airplanes. That AD currently requires repetitive inspections for cracking of certain fuselage internal structure (i.e., Sections 42 and 46 fuselage frames, upper deck floor beams, electronic bay access door cutout, nose wheel well, and main entry doors and door cutouts), and repair if necessary. This new AD requires additional repetitive inspections for cracking of certain fuselage structure (i.e., Section 41 fuselage frames where they connect to upper deck floor beams, and Section 41 fuselage frames between stringers (S-8 and S-12)), and related investigative/corrective actions if necessary. This AD also reduces the inspection threshold and repetitive inspection intervals for certain airplanes. This AD results from fatigue tests and analysis that identified additional areas of the fuselage where fatigue cracks can occur. We areissuing this AD to prevent the loss of structural integrity of the fuselage, which could result in rapid depressurization of the airplane.
57-06-02: 57-06-02 MARTIN: Applies to All Models 202, 202A and 404 Aircraft. Compliance required as indicated. As a result of a number of failures in service, the engine mount attaching studs should be replaced as indicated below: 1. Replace the engine mount studs with approved studs whenever the Quick Engine Change unit is removed for major overhaul, but at intervals not exceeding 1,600 hours flight time. Both the stud and engine mount installation should be made with care since misalinement and/or improper torque could cause failure of the stud in service. (Installation techniques are included in Martin Service Instruction Letter 404-50.) 2. If the engine mount studs are replaced with approved through-bolt installations, the replacement program of item 1 is not applicable, and this Airworthiness Directive no longer applies. 3. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and ManufacturingBranch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Martin Service Instruction Letter 202/202A of October 1, 1956, covers this same subject.) This supersedes AD 51-29-04. Revised January 11, 1963.
2009-26-01: We are adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation Model SR22 airplanes equipped with an anti- ice system approved for flight into known icing. This AD requires you to inspect the compression fittings on the anti-ice fluid distribution lines for proper installation and repair any fittings that were not properly installed. This AD results from the manufacturer finding some anti-ice fluid distribution lines where the compression fittings were not properly installed. We are issuing this AD to detect and correct anti-ice fluid distribution lines with improperly installed compression fittings, which could result in anti-ice fluid distribution line separation. A line separation could result in a total loss of ice protection fluid supply to the protected surfaces, which would allow ice to build on the airplane and degrade the handling qualities and performance.
78-22-04: 78-22-04 GENERAL DYNAMICS: Amendment 39-3326. Applies to Models 340 and 440 airplanes, including those modified for turbopropeller power in accordance with STC SA1096WE and SA4-1100, which have been modified to incorporate interiors in accordance with STC SA896EA, certificated in all categories. Compliance required as indicated. To assure release of the operator's hand after removal of the emergency exit window, accomplish the following: a. Within the next 10 hours in service after the effective date of this airworthiness directive, unless previously accomplished, remove the emergency exit interior trim panel Magee Plastics Company P/N 9675-WPE. If a replacement trim panel is installed, it must be P/N 9675- WPE-1 or an equivalent approved by the Chief, Engineering and Manufacturing Branch/FAA, Eastern Region. b. Special flight permits may be issued in accordance with FAR 21.197 to authorize operation of the aircraft to a base for the accomplishment of the modifications required by this AD. NOTE: Magee Plastics Company Service letter dated August 11, 1978, entitled "Magee Mashell Interior Kit for the Convair Part Number 96123-STC SA896EA" pertains to this subject. This amendment is effective November 1, 1978.
80-07-10: 80-07-10 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39- 3714. Applies to A109A helicopters, certificated in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent ambiguous or incorrect indication of engine operating condition, accomplish the following: (a) For those helicopters that have engine failure indicator, P/N 109-0729-22-3, installed, replace the engine failure indicator, P/N 109-0729-22-3, with a new indicator, P/N 109- 0729-22-5, and incorporate temporary pages in the Rotorcraft Flight Manual, in accordance with Agusta Bollettino Tecnico No. 109-9, dated February 23, 1978 or an equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Region. (b) For those helicopters that have engine failure indicator, P/N 109-0729-22-5, installed, unless already accomplished, incorporate temporary pagesin the Rotorcraft Flight Manual, in accordance with Agusta Bollettino Tecnico No. 109-9, dated February 23, 1978 or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region. (c) If a Rotorcraft Flight Manual includes permanent pages which incorporate the material on temporary pages 3-5 required by paragraphs (a) and (b) of this AD, the temporary pages need not be incorporated. This amendment becomes effective March 27, 1980.