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91-13-08: 91-13-08 ISRAEL AIRCRAFT INDUSTRIES (IAI): Amendment 39-7039. Docket No. 91-NM-32- AD. Applicability: Models 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent the inability to extend the nose landing gear for landing, accomplish the following: A. Remove the existing towing instruction placard and install a new placard in accordance with the applicable service bulletin, as follows: Airplane Models Service Bulletin 1121, 1121A, 1121B 1121-11-015, dated November 26, 1990 1123 1123-11-031, dated November 26, 1990 1124 and 1124A 1124-11-103, dated November 26, 1990 B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7039, AD 91-13-08) becomes effective on July 22, 1991.
72-14-01: 72-14-01 DOWTY ROTOL, LTD: Amdt. 39-1473. Applies to Dowty Rotol Propeller Types (c)R130/4-20-4/12E, (c)R186/4-30-4/16, (c)R187/4-30-4/18, (c)R193/4-30-4/50, (c)R184/4-30-4/50, (c)R259/4-40-4.5/17, (c)R148/4-20-4/21E, (c)R175/4-30-4/13E, (c)R179/4- 20-4/33, (c)R257/4-30-4/60, (c)R245/4-40-4.5/13, and (c)R209/4-40-4.5/2. These propellers are installed on, but not necessarily limited to, BAC Viscount Models 744, 745D, and 810; Armstrong Whitworth Model Argosy AW.650 Series 101; Fairchild and Fokker Models F27 and F227; Handley Page Model Herald; and Grumman Model Gulfstream G-159 airplanes. Compliance is required as indicated unless already accomplished. To prevent failure of a propeller blade due to the disengagement of the blade bearing retaining bolts resulting from excessive wear on the teeth of the locking segments, accomplish the following: Within the next 5,000 hours' time in service or at the next propeller overhaul, after the effective date of this AD, whichever occurs sooner, incorporate Dowty Rotol Modification No. (c) VP.2676 (Rev. 1) in accordance with Dowty Rotol Limited Service Bulletin No. 61-714, Revision 3, dated July 26, 1971, or an FAA-approved equivalent. This amendment becomes effective 22 July, 1972.
91-16-01: 91-16-01 MITSUBISHI HEAVY INDUSTRIES (MHI), LTD. [formerly Nihon Aeroplane Manufacturing Company (NMAC)]: Amendment 39-7091. Docket No. 91-NM-118-AD. Supersedes AD 91-06-04. Applicability: Model YS-11, YS-11A-200, YS-11A-300, YS-11A-500, and YS-11A-600 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncontrolled nose down pitch of the airplane on landing approach during icing conditions, accomplish the following: (a) Within 30 days after March 19, 1991 (the effective date of Amendment 39-6922, AD 91- 06-04), accomplish the following: (1) Revise the Operating Limitations Section of the FAA-approved Airplane Flight Manual (AFM) for the Model YS-11/-11A by adding a subparagraph B. to paragraph 1.10.5, WING DE- ICER SYSTEM, to read as follows: This may be accomplished by inserting a copy of this AD in the AFM. "B. Do not extend flaps greater than 20 degrees in the presence of known icing conditions or in visible moisture below plus 5 degrees centigrade (plus 41 degrees Fahrenheit) outside air temperature (OAT)." (2) Add a placard as near as possible to the flap handle to read as follows: "Flaps limited to 20 degrees in known icing conditions." (b) Within 30 days after the effective date of this amendment, accomplish the following: (1) Insert the following MHI Transmittal Letters in the Normal Operating Procedures Section of the AFM, as applicable: (i) For Model YS-11 airplanes: NMAC YS-11 Flight Manual Publication No. YS-FM-001, Transmittal Letter E32, dated October 2, 1990; (ii) For Model YS-11A-200 and -300 series airplanes: NMAC YS-11A- 200/300 Flight Manual Publication No. YS-FM-002, Transmittal Letter No. E2027, dated October 2, 1990; (iii) For Model YS-11A-500 series airplanes: NMAC YS-11A-500 Flight Manual Publication No. YS-FM-005, Transmittal Letter No. E5021, dated October 2, 1990; (iv) For ModelYS-11A-600 series airplanes: NMAC YS-11A-600 Flight Manual Publication No. YS-FM-006, Transmittal Letter No. E6021, dated October 2, 1990. (2) In the Normal Operating Procedures Section of the AFM, just after the MHI Transmittal Letter required by paragraph (b)(1) of this AD, revise subparagraph "(2) Flaps" of paragraph 3.1.10.1, APPROACH AND LANDING IN ICING CONDITIONS OR IN VISIBLE MOISTURE BELOW plus 5 DEGREES C (plus 41 DEGREES F) OAT, to read as follows: This may be accomplished by inserting a copy of this AD in the AFM. "(2) Flaps.............................................Set Position NOTE: Do not extend flaps greater than 20 degrees. CAUTION: IF UNUSUAL PITCHING OR YOKE MOVEMENT OCCURS WHILE EXTENDING THE FLAPS, IMMEDIATELY RETRACT THE FLAPS UNTIL THE PITCHING OR YOKE MOVEMENT STOPS." (c) An alternative method 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 (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. NOTE: Previous FAA approval granted for an alternative method of compliance with AD 91-06- 04 constitutes FAA approval as an alternative method of compliance with this AD. (d) 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. (e) The AFM revision requirements shall be accomplished, in part, by incorporating the following documents into the AFM: NMAC YS-11 Flight Manual Publication No. YS-FM-001, Transmittal Letter E32; NMAC YS-11A-200/300 Flight Manual Publication No. YS-FM-002, Transmittal Letter No. E2027; NMAC YS-11A-500 Flight Manual Publication No. YS-FM-005, Transmittal Letter No. E5021; NMAC YS-11A-600 Flight Manual Publication No. YS-FM-006, Transmittal Letter No. E6021; all of which are dated October 2, 1990. These documents contain the following list of effective pages: Publication Number/ Transmittal Letter Number Section Code Symbol Page Number Publication No. YS-FM-001 Transmittal Letter E32, dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E32 (none) (none) (none) (none) (none) 1/1 i ii-10 i 25 25a Publication No. YS-FM-002 Transmittal Letter E2027 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E2027 E101 E101 E100 E100 E100 1/1 i ii-8 i 21 22 Publication No. YS-FM-005 Transmittal Letter E5021 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/L E5021 E500 E156 E100 E100 E100 1/1 i ii-5 i 21 22 Publication No. YS-FM-006 Transmittal Letter E6021 dated October 2, 1990 Transmittal Sheet L.E.P. Log of Revision (1) 3 T/LE6021 E600 E156 E100 E100 E100 1/1 i ii-5 i 21 22 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 Nagoya Aircraft Works, Mitsubishi Heavy Industries, Ltd., 10 Oye-cho, Minato-Ku, Nagoya 455, Japan, Attention: Manager, YS-11 Group, Service Department. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. Airworthiness Directive 91-16-01 supersedes AD 91-06-04, Amendment 39-6922. This amendment (39-7091, AD 91-16-01) becomes effective on August 22, 1991.
2022-21-16: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G150 airplanes. This AD was prompted by reports that wing flap fairing debonding and corrosion were discovered at certain areas of the lower skin on both wings. This AD requires an inspection for corrosion in certain areas of the wing skin fairings, additional inspections if necessary, resealing the fairings with new fillet seal, and applicable corrective actions, as specified in a Civil Aviation Authority of Israel (CAAI) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, equipped with GE or P&W series engines. This amendment requires modifications and functional tests of the wiring of the wire integration unit and the air supply control test unit (ASCTU) of the engine bleed air distribution system. The actions specified by this AD are intended to prevent inadvertent commanded shutdown of the engine bleed air distribution systems due to an erroneous ASCTU command. This type of shutdown could cause depressurization of the airplane and subsequent ice build-up on the engine inlets during descent, which could result in ingestion of ice into the engine(s) and consequent loss of thrust on one or more engines. This action is intended to address the identified unsafe condition.
72-19-02: 72-19-02 PITTS AVIATION ENTERPRISES, INC: Amdt. 39-1518. Applies to the Pitts Model S-2A Series Airplanes, S/N 2001 through 2025. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent structural damage because of excessive in-flight vibration of the aileron interconnect tubes, accomplish the following: (a) Remove streamline aileron interconnect tubes, P/N 2-5216-1. NOTE: Make certain the length between the AN3 bolt centers for the upper and lower aileron attachments of the interconnect tube are not changed during removal. (b) Install round aileron interconnect tubes, P/N 2-5216-11. When installing the replacement tubes, make certain to adjust the length of the lower threaded end to the same overall length between AN3 bolt centers as the tubes originally installed on your airplane. Make certain that the correct number of AN960-10 (1/16 or 1/32 inch thick) washers are installed so that the bearing inner races are clamped-up snugly without bending the fork ends of the tubes. Pitts Service Bulletin No. 5, including Supplement No. 1, pertains to this same subject. This amendment becomes effective September 15, 1972.
2004-22-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspection of the metal oxide varistor (MOV) modules and transient absorption zener (TAZ) diodes to determine if those parts are outside of tolerance limits, and replacement of MOV modules and TAZ diodes with new parts, if necessary. This action is necessary to prevent the failure of critical ice protection systems following a lightning strike, which could result in reduced controllability and degraded performance of the airplane in the event of an encounter with icing conditions. This action is intended to address the identified unsafe condition.
2022-22-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that the path for the grounding wire of the engine fire shut off valve (FSOV) is routed through the wing trailing edge, which is not the shortest path available. This AD requires modifying the wiring between the inboard fixed leading edge in the wing and in the forward cargo compartment on the left- and right-hand sides, 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.
2013-15-04: We are adopting a new airworthiness directive (AD) for certain Hartzell Propeller, Inc. propeller models HC-(1,D)2(X,V,MV)20-7, HC- (1,D)2(X,V,MV)20-8, and HC-(1,D)3(X,V,MV)20-8. This AD was prompted by failures of the propeller hydraulic bladder diaphragm and resulting engine oil leak. This AD requires replacement of the propeller hydraulic bladder diaphragm. We are issuing this AD to prevent propeller hydraulic bladder diaphragm rupture, loss of engine oil, damage to the engine, and loss of the airplane.
97-02-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP airplanes, that requires repetitive inspections to detect damage of the antenna mounting reinforcing plates and surrounding fuselage skin. If any damage is detected, the AD requires replacement of the reinforcing plate with a new reinforcing plate and/or repair of the surrounding fuselage skin, which would terminate the repetitive inspection requirements. This amendment is prompted by reports of corrosion found at the antenna reinforcing plates, which was caused by the ingress of water at the plates. The actions specified by this AD are intended to prevent such corrosion, which could result in reduced structural integrity of the fuselage pressure vessel.