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76-17-07: 76-17-07 BOEING: Amendment 39-2706. Applies to Boeing Model 727-100 series airplanes certificated in all categories with static port heater circuits deactivated. Compliance required as indicated unless already accomplished. \n\tTo prevent the loss of altitude and airspeed reference due to a small amount of water freezing in the static port system, accomplish either of (1) or (2) below: \n\t(1)\tWithin the next 1,000 hours time in service after the effective date of this AD reactivate the static port heater circuits to the original FAA approved Boeing 727-100 configuration; or \n\t(2)\tWithin the next 2,000 hours time in service after the effective date of this AD replace the deactivated heater assembly, P/N 10-60723-1, with elbow fitting MS21908D6 in accordance with Boeing Service Bulletin 727-34-95 dated September 3, 1976, or later FAA approved service bulletins, and enlarge the static port sensing holes from .047 inch diameter to .125 inch diameter in accordance with Boeing ServiceBulletin 727-34-94 (to be released) or later FAA approved service bulletins. \n\tNotwithstanding the provisions of the above paragraph (1) the heater elements in one static system may be inoperative provided the aircraft is not flown in icing or precipitation conditions. \n\tBoeing 727-100 airplanes already incorporating Boeing Service Bulletin 727-25-42, Revision 1, dated March 4, 1968, with elbow fitting MS21908D6 and Boeing Service Bulletin 727-34-57 dated April 7, 1968, enlarging the static sense holes are in compliance with this AD. \n\tEquivalent modifications may be approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe 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). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective October 1, 1976.
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96-22-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe series 1000A and Model Hawker 1000 airplanes, that requires modifications of the thrust reversers. This amendment is prompted by a review of the certification analysis of the thrust reversers and by testing of the thrust reversers, which indicated that additional design features are necessary to prevent failure of the driver link and the inadvertent deployment of a thrust reverser during flight. The actions specified by this AD are intended to prevent inadvertent deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.
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96-22-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Models 1900C, 1900D, and 2000 airplanes. This action requires inspecting (one-time) the fuel filter assemblies to detect any bypass valve that is glued shut. If a bypass valve is glued shut, the AD requires replacing the associated fuel filter assembly. Three in-flight occurrences in which the low fuel pressure light illuminated prompted this action. In each of the instances, a bypass valve on the affected airplane engine was glued shut with anaerobic thread lock adhesive and when the fuel filter became clogged, proper fuel flow to the engine was not obtained. The actions specified by this AD are intended to prevent lack of fuel to the engine and eventual engine shutdown caused by a clogged fuel filter and a contaminated fuel filter bypass valve.
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93-07-04: 93-07-04 BRITISH AEROSPACE: Amendment 39-8536. Docket 92-NM-189-AD.
Applicability: Model ATP series airplanes; serial numbers 2001 through 2049, inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished previously.
To prevent possible loss of integrity and security of the flap drive system, accomplish the following:
(a) Within 14 days after the effective date of this AD, perform a one-time general visual inspection of the primary flap drive torque tubes to ensure that the four bolt and nut assemblies on the splined flanged-coupling assembly on the right gearbox drive at station 0 have split pins installed, in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992.
(1) If split pins are installed, no further action is necessary.
(2) If any split pin is missing, accomplish the requirements of both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD:
(i) Prior to further flight, check tighten each of the four bolts to 8 to 10 foot pounds torque. Repeat this check tightening thereafter at intervals not to exceed 14 days.
(ii) Within 6 months after the effective date of this AD, install split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. Installation of these split pins constitutes terminating action for the inspections and check tightening requirements of this paragraph.
(b) Installation of split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992, constitutes terminating action for the requirements of paragraph (a) of this AD.
(c) 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. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, 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.
(d) 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.
(e) The inspection and installation shall be done in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 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 Jetstream Aircraft, Inc., Librarian for Service Bulletins, P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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.
(f) This amendment becomes effective on May 10, 1993.
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2021-07-14: The FAA is adopting a new airworthiness directive (AD) for all Yabora Industria Aeronautica S.A. Model EMB-135 and EMB-145 airplanes. This AD was prompted by a report involving disconnection of a side arm strut from the right main landing gear (MLG); a subsequent investigation found that the side arm strut lower bearing was installed inverted on the airplane. This AD requires doing a general visual inspection of the right and left MLG to verify certain conditions and doing all applicable on-condition actions, as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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91-23-12: 91-23-12 LOCKHEED: Amendment 39-8081. Docket No. 91-NM-77-AD.
Applicability: Model L-1011 series airplanes, equipped with BFGoodrich brake part numbers identified in paragraph (a) of this AD, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent the loss of main landing gear braking effectiveness, accomplish the following:
(a) Within 180 days after the effective date of this AD, inspect the brake part numbers shown below for wear. Any brake worn more than the maximum wear limit specified below must be replaced, prior to further flight, with a brake within this limit.
Type Certificated
Model Designation
Common Model
Designation
Maximum
GTOW
Brake
Part No.
Maximum Wear
Limit (inches)
L-1011-385-1
(-1)
430,000
2-1195-1
2.10
(-1)
430,000
2-1195-5
2.10
(-1)
430,000
2-1195-6
2.10
(-1)
430,000
2-1195-7
2.10
(-1)
430,000
2-1195-8
2.10
(-1)
430,000
2-1367
3.00
(-1)
430,000
2-1367-1
3.00
(-1)
430,000
2-1367-2
3.00
(-40)
440,000
2-1195-1
2.10
(-40)
440,000
2-1195-5
2.10
(-40)
440,000
2-1195-6
2.10
(-40)
440,000
2-1195-7
2.10
(-40)
440,000
2-1195-8
2.10
(-40)
440,000
2-1367
3.00
(-40)
440,000
2-1367-1
3.00
(-40)
440,000
2-1367-2
3.00
(-50)
450,000
2-1367-3
2.60
(-50)
450,000
2-1367-4
2.60
(-50)
450,000
2-1367-5
2.60
L-1011-385-1-14
(-100,-150,-200)
466,000
2-1367-3
2.60
(-100,-150,-200)
to
2-1367-4
2.60
(-100,-150,-200)
474,000
2-1367-5
2.60
(-250)
510,000
2-1367
3.00
(-250)
510,000
2-1367-1
3.00
(-250)
510,000
2-1367-2
3.00
L-1011-385-1-15
(-100,-150,-200)
466,000
2-1367-3
2.60
(-100,-150,-200)
to
2-1367-4
2.60
(-100,-150,-200)
474,000
2-1367-5
2.60
(-250)
510,000
2-1367
3.00
(-250)
510,000
2-1367-1
3.00
(-250)510,000
2-1367-2
3.00
L-1011-385-3
(-500)
496,000
2-1367
3.00
(-500)
to
2-1367-1
3.00
(-500)
516,000
2-1367-2
3.00
NOTE: Lockheed Service Bulletin 093-32-253, dated March 29, 1991, contains additional information concerning Model L-1011 brake configurations.
(b) Within 180 days after the effective date of this AD, incorporate the maximum brake wear limits specified in paragraph (a) of this AD into the FAA-approved maintenance inspection program.
(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.
(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.
This amendment (39-8081, AD 91-23-12) becomes effective on December 9, 1991.
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96-21-10: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
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96-21-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that requires either replacement or modification of the hydraulic damper assembly. This amendment is prompted by reports indicating that insufficient damping of the hydraulic shimmy damper in the main landing gear (MLG) can allow high torsional vibration to occur. The actions specified by this AD are intended to prevent such vibration, which can damage the MLG assembly and lead to its collapse.
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93-04-02: 93-04-02 ROCKWELL INTERNATIONAL/COLLINS AVIATION DIVISION: Amendment 39-8504. Docket No. 93-CE-18-AD.
Applicability: TDR-94D Mode S transponders, P/N CPN 622-9210-002, installed on, but not limited to the following, certificated in any category:
Aerospatiale ATR-42 and ATR-72 series airplanes
Saab 340A and 340B airplanes
Short Model SD3-60 airplanes
de Havilland DHC-7 and DHC-8 series airplanes
British Aerospace ATP airplanes
Gulfstream G-II, G-III, and G-IV series airplanes
Dassault Mystere-Falcon 50, Mystere-Falcon 200,
and Mystere-Falcon 900 airplanes
Canadair Challenger CL-601 airplanes
British Aerospace HS 125-700A airplanes
Beechcraft 300 series airplanes
Compliance: Required as indicated, unless already accomplished.
To prevent a mid-air collision or a near-miss situation caused by failure of these Mode S transponders, accomplish the following:
(a) Within the next 10 calendar days after theeffective date of this AD, fabricate a placard with the following words in letters at least 0.10-inch in height and install this placard within the pilot's clear view on the instrument panel: "OPERATION OF TCAS II IN ANY MODE OTHER THAN THE "TA ONLY" MODE IS PROHIBITED."
(b) Within the next 6 calendar months after the effective date of this AD, modify the software of the Mode S transponders in accordance with the Accomplishment Instructions section of Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. The placard required by paragraph (a) of this AD is no longer required after this modification is incorporated.
(c) If parts for the above modification are not available, the airplane operator may comply with the placard requirement of paragraph (a) of this AD until the modification is incorporated based upon a schedule established by the manufacturer through the Atlanta Aircraft Certification Office.
(d) Special flight permits may be issuedin accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office.
(f) The modification required by this AD shall be done in accordance with Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 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 Rockwell International/Collins General Aviation Division, 1100 West Hibiscus Boulevard, Melbourne, Florida 32901. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., 7th Floor, suite 700, Washington, DC.
(g) This amendment becomes effective on March 26, 1993.
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2021-07-03: The FAA is superseding Airworthiness Directive (AD) 2015-05- 03, which applied to certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015-05-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations, and incorporating structural repairs and modifications to preclude widespread fatigue damage (WFD). This AD continues to require the actions specified in AD 2015-05-03. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and incorporating additional structural repairs and modifications to preclude WFD. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary, as well as the corresponding structural repairs and modifications to preclude WFD. The FAA is issuing this AD to addressthe unsafe condition on these products.
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