Aircraft-logs.com

Results
2021-08-12: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by crack indications found in the lower aft wing skin bolt holes where the flap tracks attach to the track support fitting. This AD requires repetitive inspections for cracking of the left and right wing, lower aft wing skin aft edge, at certain flap track locations, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
91-09-08: 91-09-08 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6975. Docket No. 90-NM-275-AD. Supersedes AD 80-22-14. Applicability: Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent structural fatigue failure of the fuselage longeron at the rear spar frame and the lower wing/outboard nacelle joint, accomplish the following: A. For airplanes Serial Numbers 1 through 14, with 2,975 hours or more time-in- service: Within the next 25 hours time-in-service, after October 31, 1980 (the effective date of Amendment 39-3961, AD 80-22-14), unless previously accomplished within the last 975 hours time-in-service, perform a radiographic inspection for cracks at the rear spar wing attachment to the fuselage frame in accordance with the instructions given in Figures 1 and 2 of de Havilland Service Bulletin 7-53-9, dated May 23, 1980. NOTE: Inspections performed in accordance with de Havilland Service Bulletin 7-53-9, Revision A, dated June 9, 1980, or Revision B, dated September 10, 1982, are considered in compliance with the requirements of this paragraph. 1. If cracks are found, prior to further flight, repair in a manner approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, New England Region, and incorporate de Havilland Modification No. 7/1622 (reinforcement of the rear spar frame) in accordance with the Accomplishment Instructions of the service bulletin. 2. If no cracks are found, repeat the radiographic inspection at intervals not to exceed 1,000 hours time-in-service. B. For airplanes Serial Numbers 1 through 14 and 17, with 4,975 hours or more time-in-service: Within the next 25 hours time-in-service, after October 31, 1980 (the effective date of Amendment 39-3961, AD 80-22-14), unless previously accomplished within the last 975 hours time-in-service, perform a radiographic inspection for cracks at the wing/outboard nacelle joint in accordance with the instructions given in Figure 1 of DeHavilland Service Bulletin 7-57- 4, dated May 23, 1980. NOTE: Inspections performed in accordance with de Havilland Service Bulletin 7-57-4, Revision A, dated September 10, 1982, are considered in compliance with the requirements of this paragraph. 1. If cracks are found, prior to further flight, repair in a manner approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA, New England Region, and incorporate DeHavilland Modification No. 7/1645 (reinforcement of the lower wing structure and outboard nacelle) in accordance with the Accomplishment Instructions of the service bulletin. 2. If no cracks are found, repeat the radiographic inspection at intervals not to exceed 1,000 hours time-in-service. C. Within 2 years after the effective date of this AD, reinforce the longeron at the rear spar frame (Modification No. 7/1622) and reinforce the wing/nacelle joint (Modification No. 7/1645), in accordance with the Accomplishment Instructions in de Havilland Service Bulletins 7-53-9, Revision B, and 7-57-4, Revision A, both dated September 10, 1982. Accomplishment of Modifications 7/1622 and 7/1645 constitutes terminating action for the repetitive radiographic inspections required by paragraphs A. and B. of this AD. D. 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. E. 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 of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. Airworthiness Directive 91-09-08 supersedes AD 80-22-14, Amendment 39-3961. This amendment (39-6975, AD 91-09-08) becomes effective on May 28, 1991.
76-14-02: 76-14-02 DEHAVILLAND AIRCRAFT of CANADA, LTD: Amendment 39-2663. 1. Applies to DHC-2 (L-20A, YL-20, U-6A) Airplanes, Serial Numbers 1 thru 1335 except 1283, 1318 and 1324, certificated in all categories, but not altered in accordance with DeHavilland Modification 2/1420. Compliance required within the next 50 hours in service after the effective date of this AD. Inspect for cracks and, if necessary, replace the fin pick-up front casting, P/N C2TF57, in accordance with paragraph "PROCEDURE" in DeHavilland Aircraft, Ltd., Engineering Bulletin, Series "B", No. 22, or an approved equivalent alteration. 2. Applies to DHC-2 MK III Turbo-Beaver Airplanes, Serial Numbers 3 thru 5, 7 thru 29, 31 thru 35, 37 thru 39, 41, 43, 44, 46, 48, 50, 52 and 54, certificated in all categories. Compliance required within the next 25 hours in service after the effective date of this AD, unless already accomplished. Repair the rudder horn skin and horn rib flanges in accordance with paragraph "PROCEDURE" in DeHavilland Modification Bulletin No. T2/2061 or an approved equivalent repair. 3. Applies to all DHC-2 MK III float or amphibious float equipped Turbo-Beaver Airplanes, except Serial Numbers 1662-TB36, 1684-TB52, 1686-TB54 and subsequent, certificated in all categories. Compliance required as indicated, unless already accomplished. a. Prior to further flight the following placard will be placed in clear view of the pilot: "Gross weight at forward C.G. limits restricted to 4000 pounds. b. Upon alteration of the top and bottom caps of the horizontal stabilizer rear spar, in accordance with paragraph "PROCEDURE" in DeHavilland Modification Bulletin No. T2/2059, the placard required in paragraph (a) may be removed. 4. Applies to DHC-2 (L-20A, YL-20, U-6A) Airplanes, Serial Numbers 1 thru 9, certificated in all categories, unless already accomplished. Compliance required within the next 25 hours in service after the effective date of this AD. Visually inspect and, if necessary, replace the three attachment bolts on the tailwheel assembly in accordance with the 2d and 3rd paragraphs in DeHavilland Aircraft, Ltd., Technical News Sheet, Series B, No. 1, or an approved equivalent alteration. 5. Applies to DHC-2 (L-20A, YL-20, U-6A) float equipped Airplanes, Serial Numbers 1 thru 14, certificated in all categories, unless already accomplished. Compliance required within the next 25 hours in service after the effective date of this AD. Reinforce the front float pick-up fitting on the fuselage at the firewall with DeHavilland P/N C2-FS-3381, in accordance with paragraph 3. and 4. in DeHavilland Aircraft, Ltd. Technical News Sheet, Series B, No. 3, or an approved equivalent alteration. 6. Applies to DHC-2 (L-20A, YL-20, U-6A) Airplanes, Serial Numbers 1 thru 61 and 63, certificated in all categories, unless already accomplished. (a) Prior to next flight, visually inspect the No. 10-32 mounting screws at each elevator mass balance weight for looseness and thereafter on a daily basis. (b) Any loose No. 10-32 mounting screws must be replaced, in accordance with the applicable numbered paragraphs 1 thru 10 in DeHavilland Aircraft, Ltd., Technical News Sheet, Series B, No. 20 (Mod. 2/384) or an approved equivalent alteration. (c) Upon replacement of all the No. 10-32 mounting screws, in accordance with procedure specified in (b), the daily inspections may be discontinued. 7. Applies to DHC-2 (L-20A, YL-20, U-6A) Airplanes, Serial Numbers 1 thru 66, certificated in all categories, unless already accomplished. Compliance required within the next 25 hours in service after the effective date of this AD. a. Reinforce rudder with DeHavilland P/N C2-TR-123 in accordance with numbered paragraphs 1 thru 3 in DeHavilland Aircraft, Ltd., Technical News Sheet, Series B, No. 22 or an approved equivalent repair. b. Visually inspect rudder nose skinformer P/N C2-TR-47ND and if cracks are found, replace former with an unused part, using 1/8" cherry rivets - 8 required, in accordance with DeHavilland Aircraft, Ltd., Technical News Sheet, Series B, No. 22 sketch or an approved equivalent repair. 8. Applies to DHC-2 (L-20A, YL-20, U-6A) Airplanes, Serial Numbers 1 thru 9, 11 thru 13, 15 thru 50, 52 thru 61, 63, 64 and 66, certificated in all categories, unless already accomplished. Compliance required within the next 25 hours in service after the effective date of this AD. Replace the original main undercarriage tie bolt locking pins, P/N C2-U-381, with unused 3/8" diameter locking pins in accordance with the sixth paragraph and continuing thru g) iii) in DeHavilland Aircraft, Ltd., Technical News Sheet, Series B, No. 25 (Mod. 2/333) or an approved equivalent alteration. 9. Applies to all DHC-2 (L-20A, YL-20, U-6A) Airplanes equipped with Federal Aircraft Works AWB-4820 wheel-ski installation, certificated in allcategories, unless already accomplished. Compliance required before the next flight and every 50 hours in service thereafter, after the effective date of this AD. Inspect the AN5-24 bolt which secures Federal ski axle, P/N 10B1868 and Beaver wheel axle, P/N C2-U-193, to the undercarriage leg structure, for distortion or wear. Distorted or worn bolts are to be replaced with new AN5-24 bolts or approved equivalent bolts prior to further flight. 10. Applies to all DHC-2 (L-20A, YL-20, U-6A) Airplanes equipped with early model Federal Aircraft Works AWB-4820 wheel-skis, certified in all categories, unless already accomplished. The early model wheel-skis can be identified by a "T" shape aft arm stop welded to the saddle. This AD does not apply to the later model wheel-skis which have an inverted "U" shape aft arm stop welded to the saddle. Compliance required within the next 25 hours in service after the effective date of this AD. Incorporate the modification covering the installation of an aft arm stop bracket, in accordance with Federal Aircraft Works Drawing No. 10D2506 or an approved equivalent alteration. 11. Applies to all DHC-2 (L-20A, YL-20, U-6A) Airplanes equipped with DeHavilland Aircraft, Ltd. combination wheel-skis, certificated in all categories, unless already accomplished. Compliance required as indicated: (a) Prior to the next ski installation or prior to next flight with combination wheel-skis, inspect left and right retractable ski axle pin bushings, P/N C3US149-3, for excessive play or seizure in accordance with paragraphs 1, 2, 3, 14.2 and 14.3, in Dehavilland Aircraft, Ltd., Engineering Bulletin, Series B, No. 24, Issue 2 or an approved equivalent inspection. (b) Bushings that are not worn may be retained in service provided that the area is adequately lubricated and the inspection specified in (a) is repeated at intervals not to exceed 100 hours in service from the previous inspection. (c) Upon replacement of the ski axle pins and bushings, in accordance with numbered paragraphs 1. thru 13. under "PROCEDURE" in de Havilland Aircraft, Ltd., Engineering Bulletin, Series B, No. 24, Issue 2, including amendment No. 1 (Mod No. 2/1438), the 100 hour inspections may be discontinued. Equivalent placards, signs, parts, inspections, procedures, instructions, repairs, alterations and modifications, as applicable, must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Upon request, with substantiating data submitted through an FAA maintenance inspector, the compliance times of this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Compliance with the Airworthiness Directive must be noted in the log book of the aircraft by referencing the Airworthiness Directive number and the specific item complied with: i.e. AD 76 - - - (4) if item 4 is being complied with. This amendment is effective July 12, 1976.
97-05-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269A-2, and 269B helicopters, that currently requires initial and repetitive inspections of the main rotor thrust bearing (bearing) for bearing rotational roughness, corrosion, inadequate lubrication, physical damage, or excessive zinc chromate paste or moisture. This amendment requires the same initial and repetitive inspections required by the existing AD, but would extend the retirement life for certain bearings, and would remove the Model 269A-2 helicopter from, and add the Model TH-55A helicopters to the applicability of this AD. This amendment is prompted by an FAA analysis of service information issued by the manufacturer that extends the retirement life for certain bearings. The actions specified by this AD are intended to prevent failure of the bearing, loss of the main rotor, and subsequent loss of control of the helicopter.
2004-03-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, - 201, -202, -301, -311, and -315 airplanes, that currently requires a one-time inspection to detect chafing of electrical wires in the cable trough below the cabin floor; repair, if necessary; installation of additional tie-mounts and tie-wraps; and application of sealant to rivet heads. This amendment requires adding an additional modification of the electrical wires in certain sections. The actions specified by this AD are intended to prevent chafing of electrical wires, which could result in an uncommanded shutdown of an engine during flight. This action is intended to address the identified unsafe condition.
2021-08-04: The FAA is superseding Airworthiness Directive (AD) 2013-07- 09, which applied to certain The Boeing Company Model 737-700, -700C, - 800, and -900ER series airplanes, Model 747-400F series airplanes, and Model 767-200 and -300 series airplanes. AD 2013-07-09 required a general visual inspection for affected serial numbers of the crew oxygen mask stowage box units, and replacement or re-identification as necessary. This AD retains the requirements of AD 2013-07-09 and expands the applicability. This AD was prompted by a determination that the affected parts may be installed on airplanes outside the original applicability of AD 2013-07-09. The FAA is issuing this AD to address the unsafe condition on these products.
89-03-02: 89-03-02 FOKKER: Amendment 39-6121. Applicability: Model F-28 series airplanes, Serial Number 11003 through 11231, 11991, and 11992, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a potential fire hazard in the cockpit, accomplish the following: A. Within 60 days after the effective date of this AD, relocate the instrument lighting ballast transformers from the glareshield panel and the right-hand cockpit sidewall to the left-hand cockpit sidewall, in accordance with Fokker Service Bulletin No. F28/33-34, dated June 1, 1988. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments 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 for the accomplishment of the modification required by 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 Fokker Aircraft, USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6121, AD 89-03-02) becomes effective March 6, 1989.
97-04-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires modification of the aileron centering spring and trim mechanism. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent jamming of the aileron control system during flight due to fracturing of the springs in the aileron centering units; this condition, if not corrected, could result in reduced lateral control of the airplane.
97-03-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes, Model MD-88 airplanes, and C-9 (military) series airplanes, that requires modification of the girt and firing lanyard stowage. This amendment is prompted by reports of in-cabin inflation of certain evacuation slides due to the impingement of the galley service cart on the slide girt and firing lanyard. The actions specified by this AD are intended to prevent inadvertent inflation of the evacuation slides inside the cabin, which could contribute to injury of passengers and/or flightcrew in the passenger cabin.
91-20-05: 91-20-05 BRITISH AEROSPACE: Amendment 39-8039. Docket No. 91-NM-110-AD. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of cabin pressurization, accomplish the following: (a) For airplanes operated to a maximum of 7.5 pounds per square inch (psi) cabin pressure differential: Prior to the accumulation of 24,000 landings, or within 3,000 landings after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 3,200 landings; perform a visual inspection of the skin and cleats at the front and rear extremities of the twelve stiffeners to detect cracks, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. (b) For airplanes modified for operation to a maximum of 8.2 psi cabin pressure differential: Prior to the accumulation of 16,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 2,400 landings; perform a visual inspection of the skin and cleats at the front and rear extremities of the twelve stiffeners to detect cracks, in accordance with the British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. (c) If skin cracks are found, prior to further flight, repair in accordance with a procedure approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. If cleat cracks are found, prior to further flight, replace cracked cleats by installing a new part having post-Modification PM5629 Part (a) configuration. (d) For all airplanes: Prior to the accumulation of 85,000 landings, install Modification PM5629 Part (a) in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. (e) Installation of Modification PM5629 Part(a), in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991, constitutes terminating action for the repetitive inspections required by paragraphs (a) and (b) of this AD. (f) 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. (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. (h) The inspection, repair, and installation requirements shall be done in accordance with British Aerospace Alert Service Bulletin 53-A-PM5990, Issue 1, dated January 7, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8039, AD 91-20-05) becomes effective on November 7, 1991.