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2024-17-04: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report of a missing pintle fuse pin in the left-hand (LH) main landing gear (MLG) discovered during scheduled maintenance. This AD requires doing an inspection of the MLG pintle housing assembly to verify that the pintle fuse pins are present and correctly installed, and corrective actions if necessary, as specified in a Transport Canada Emergency AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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2017-01-12: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Model DA 42 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 an uncommanded engine shutdown during flight due to failure of the propeller regulating valve caused by hot exhaust gases escaping from fractured engine exhaust pipes. We are issuing this AD to require actions to address the unsafe condition on these products.
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98-01-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires replacement of the main landing gear (MLG) uplocks with new or modified MLG uplocks. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the MLG to lock in the stowed position due to ice accumulation on the uplock hook and roller assembly, which could result in the inadvertent deployment of the MLG during flight.
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2021-09-05: The FAA is superseding Airworthiness Directive (AD) 2016-08-20 for certain Airbus Helicopters (previously Eurocopter France) EC130B4 and EC130T2 helicopters. AD 2016-08-20 required repetitively inspecting the tail boom to Fenestron junction frame (junction frame) for a crack. This new AD continues to require inspecting the junction frame with the horizontal stabilizer removed, and expands the applicability, revises the compliance time and the inspection procedures for inspecting the junction frame, adds inspection procedures for certain helicopters, allows repair of the junction frame, and requires modifying and then repetitively inspecting the junction frame and reporting certain information. This AD was prompted by additional cracks and the availability of a design change that modifies the junction frame. The actions of this AD are intended to address an unsafe condition on these products.
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2017-01-10: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model C-212 airplanes. This AD was prompted by multiple reports of damaged and cracked rudder torque tube shafts. This AD requires various repetitive inspections, and corrective actions if necessary. This AD also provides a modification which terminates the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
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78-09-09: 78-09-09 DETROIT DIESEL ALLISON: Amendment 39-3207. Applies to 501-D13/501-D13A/501- D13D/501-D13E, and 501-D13H engines equipped with third stage turbine wheel P/N's 6788833, 6842143, 6841223, and 6846553 or fourth stage turbine wheel P/N's 6738424 and 6843014 installed in aircraft certificated in all categories.
Compliance required as follows unless previously accomplished:
To preclude possible engine failure resulting from third or fourth stage turbine wheel failure: Remove and classify all third and fourth stage turbine wheels with unknown carbide precipitation classifications in accordance with the compliance times specified in (a) and (b) below, and the procedures specified in Detroit Diesel Allison Commercial Overhaul Information Letter No. 349 Rev. 1 or later FAA approved revision. Wheels both newly and previously classified with carbide precipitation classifications of "Heavy" must be removed from service in accordance with the maximum life limits specified in (a) and (b) below. Wheels both newly and previously classified with carbide precipitation classifications of "Medium Heavy" must be removed from service in accordance with the maximum life limits specified in (c) through (h) below. Wheels of all other classifications may be returned to service and operated in accordance with the existing hourly life limits.
(a) For wheels of "Heavy" and unknown carbide precipitation classification which exceed 8000 total cycles upon the effective date of this AD, compliance is required within 300 cycles.
(b) For wheels of "Heavy" and unknown carbide precipitation classification which do not exceed 8000 total cycles upon the effective date of this AD, compliance is required prior to reaching 8300 total cycles.
(c) For wheels of "Medium Heavy" carbide precipitation classification which exceed 16,000 total cycles upon effective date of this AD, compliance is required within 200 cycles.
(d) For wheels of "Medium Heavy" carbide precipitation classification which have from 14,000 to 16,000 total cycles upon the effective date of this AD, compliance is required within the next 400 cycles or prior to exceeding 16,200 cycles whichever occurs first.
(e) For wheels of "Medium Heavy" carbide precipitation classification which have from 10,500 to 14,000 total cycles upon the effective date of this AD, compliance is required within the next 1000 cycles or prior to exceeding 14,400 total cycles whichever occurs first.
(f) For wheels of "Medium Heavy" carbide precipitation classification which have from 8000 to 10,500 total cycles on the effective date of this AD, compliance is required within the next 2000 cycles or prior to exceeding 11,500 total cycles whichever occurs first.
(g) For wheels of "Medium Heavy" carbide precipitation classification which have from 7000 to 8000 total cycles on the effective date of this AD, compliance is required prior to exceeding 10,000 cycles.
(h) For wheels of "Medium Heavy" carbide precipitation classification which do not exceed 7000 total cycles upon the effective date of this AD, compliance is required prior to exceeding 8000 cycles.
NOTE: For purposes of this airworthiness directive a cycle is defined as one takeoff.
The Detroit Diesel Allison Commercial Overhaul Information Letter identified in this directive is incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). The Detroit Diesel Allison Commercial Overhaul Information Letter incorporated herein may be obtained upon request to Detroit Diesel Allison, Division of General Motors Corporation, P.O. Box 894, Indianapolis, Indiana 46206. This document may also be examined at the FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and the Great Lakes Region. (Detroit Diesel Allison Commercial Service Letter 501-D13 CSL-253 also pertains to this subject.)
This amendment becomes effective May 12, 1978.
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76-02-04: 76-02-04 BRITTEN NORMAN LTD: Amendment 39-2499. Applies to BN-2A and BN-2A Mark III airplanes, all series, certificated in all categories, equipped with engine mounting frames P/N's NB-20-D-5209, NB-20-G-1901, NB-20-G-5231, or NB-51-H-1021.
Compliance is required as indicated.
To prevent failure of the engine mounting frame and possible physical separation of the engine, accomplish the following:
(a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the welds on the engine mounting frame around the periphery of the mounting pads for cracks and the mounting pads for conformance to the dimensions set forth in the first paragraph of the section entitled "Inspection" of Britten Norman Service Bulletin No. BN-2/SB.72, dated March 27, 1974, or an FAA-approved equivalent.
(b) As a result of the inspection required by paragraph (a) of this AD, if two or more of the engine mounting pads are foundnot to conform to all of the dimensions specified in Britten Norman Service Bulletin No. BN-2/SB.72, dated March 27, 1974, prior to further flight, replace the engine mounting frame in accordance with paragraph (e) of this AD.
(c) As a result of the inspection required by paragraph (a) of this AD, if one of the engine mounting pads is found not to conform to all of the dimensions specified in Service Bulletin No. BN-2/SB.72, visually inspect the welds around the periphery of the mounting pads prior to the first flight of each day, until the engine mounting frame is replaced in accordance with paragraph (e) of this AD.
(d) If a crack is found as a result of an inspection required by paragraphs (a) or (c) of this AD, before further flight, replace the engine mounting frame in accordance with paragraph (e) of this AD.
(e) Where required or authorized by paragraph (b), (c), or (d) of this AD, replace the engine mounting frame with a serviceable engine mounting frame of the same part number that has been inspected and found to have no cracks in the welds around the periphery of the mounting pads and found to conform to all of the dimensions specified in the "Inspection" paragraph of Britten Norman Service Bulletin No. BN-2/SB.72 dated March 27, 1974, or an FAA-approved equivalent.
This amendment becomes effective January 30, 1976.
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77-17-08: 77-17-08 AVCO LYCOMING: Amendment 39-3019 as amended by Amendment 39-3165. Applies to all Avco Lycoming T53 series engines.
Compliance for P/Ns 1-170-240-52, 1-170-240-58, and 1-170-240-59 is required by September 15, 1977.
Compliance for remaining part numbers listed below is required by May 1, 1978.
To preclude possible failure of the fuel regulator P1 multiplier lever resulting in flameout of the engine, perform the following in accordance with Avco Lycoming Service Bulletin No. 0048, Revision 1, dated March 15, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region:
1. Fill the fuel regulator P1 multiplier cavity with silicone oil, General Electric P/N SF96-100, or equivalent.
2. Reidentify the fuel regulator, from P/N 1-170-240-52 to P/N 1-170-240-61, or from P/N 1-170-240-58 to P/N 1-170-240-60, or from P/N 1-170-240-59 to P/N 1-170-240-62.
From P/N To P/N
1-160-840-01 1-160-840-15
1-160-840-02 1-160-840-14
1-160-840-03 1-160-840-13
1-160-840-09 1-160-840-11
1-160-840-10 1-160-840-12
1-160-950-02 1-160-950-16
1-160-950-04 1-160-950-15
1-160-950-05 1-160-950-17
1-160-950-06 1-160-950-18
1-160-950-08 1-160-950-19
1-160-950-10 1-160-950-13
1-160-950-12 1-160-950-14
1-170-240-01 1-170-240-68
1-170-240-03 1-170-240-69
1-170-240-04 1-170-240-70
1-170-240-05 1-170-240-71
1-170-240-06 1-170-240-72
1-170-240-08 1-170-240-73
1-170-240-09 1-170-240-74
1-170-240-12 1-170-240-75
1-170-240-17 1-170-240-76
1-170-240-19 1-170-240-77
1-170-240-20 1-170-240-78
1-170-240-21 1-170-240-64
1-170-240-25 1-170-240-79
1-170-240-26 1-170-240-80
1-170-240-27 1-170-240-81
1-170-240-30 1-170-240-82
1-170-240-45 1-170-240-63
1-170-240-46 1-170-240-83
1-170-240-47 1-170-240-84
1-170-240-48 1-170-240-67
1-170-240-49 1-170-240-65
1-170-240-57 1-170-240-66
The manufacturer's Service Bulletin identified and described in this directive is 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 Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06497. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C.
A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C., and at New England Region.
Amendment 39-3019 became effective August 31, 1977.
This amendment 39-3165 becomes effective March 30, 1978.
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75-05-06: 75-05-06 PRATT & WHITNEY AIRCRAFT: Amendment 39-2099 as amended by Amendment 39-2604 is further amended by Amendment 39-2814. Applies to all Pratt & Whitney Aircraft JT8D model engines containing P/Ns 629141, 629148, 629154, 699155, 735780, and 735781 fuel manifolds with fuel manifold "B" nuts which have not been retorqued in service.
To preclude possible fuel manifold leakage accomplish the following:
1. Retorque the fuel manifold "B" nuts in accordance with Pratt and Whitney Aircraft Service Bulletin 4389, Revision 7, or later FAA approved revision or Section 72-37 of Pratt and Whitney Aircraft JT8D Engine Manual No. 481672, Revision 78, or later FAA approved revision within the next 1500 hours time in service after March 12, 1976, for fuel manifolds with "B" nuts which were single or double torqued at original manufacture and within the next 1500 hours time in service after the effective date of this amendment for fuel manifolds with "B" nuts which were quadruple torqued at original manufacture, unless already accomplished.
2. Until the fuel manifold "B" nuts are retorqued in accordance with Paragraph 1, accomplish the following inspection once a day on engines with over 1000 hours total time in service since new:
a. Within 20 minutes after engine shutdown, inspect the inside diameter of the diffuser fan duct, combustion chamber fan duct, exhaust fan duct, and exhaust nozzle for evidence of residual fuel wetness or staining, using a six volt light source or equivalent. Direct the light source into the engine tailpipe to illuminate the fan duct as far forward as the diffuser case. If residual fuel is not evident, inspect within 30 minutes after engine shutdown for the presence of dripping fuel at the diffuser fan duct and combustion chamber fan duct flanges and for the presence of fuel in the cowl bottom quadrant under these flanges.
b. Remove from service before further flight those engines that have evidence of fuel leakage.3. Equivalent methods approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may be substituted for torquing the fuel manifold "B" nuts and for compliance with the requirements of Paragraph 1 and 2.
NOTE: Pratt & Whitney Aircraft Alert Service Bulletin No. 4389, dated January 16, 1975, pertains to this subject.
The manufacturer's engine manual 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 Pratt & Whitney Aircraft, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington, D.C., and at the New England Regional office in Burlington, Massachusetts.
Upon submission of substantiating data through an FAA maintenance inspector by an owner or operator, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time.
Amendment 39-2099 became effective March 12, 1975.
Amendment 39-2604 became effective May 20, 1976.
This amendment 39-2814 becomes effective February 24, 1977.
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2016-26-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the nose wheel well is subject to widespread fatigue damage (WFD). This AD requires modification, inspections, and corrective actions of the nose wheel body structure. We are issuing this AD to address the unsafe condition on these products.
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