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78-08-06: 78-08-06 BRITISH AIRCRAFT CORPORATION: Amendment 39-3186. Applies to Model BAC 1-11 200 and 400 Series airplanes certificated in all categories, which have a rear passenger door installed in the aft pressure bulkhead.
Compliance is required as indicated.
To detect cracking and prevent possible failure of the door structure under pressure loads, accomplish the following:
(a) Prior to accumulating 30,000 landings or within 800 flight hours time in service after the effective date of this AD, whichever occurs later, unless accomplished within the last 800 flight hours, and thereafter at intervals not to exceed 800 flight hours from the last crackfree inspection, inspect the passenger door in the aft pressure bulkhead for cracks in accordance with paragraph 2.2 of the section entitled "Accomplishment Instructions" of British Aircraft Corporation Alert Service Bulletin 52-A-PM5448, issue 2, dated July 4, 1977, or an FAA-approved equivalent.
(b) If horizontal cracks arefound during the inspection required by paragraph (a) of this AD which do not exceed the combined limitations of (b)(1) and (b)(2) noted below, the doors may remain in service provided the cracks are stop drilled and inspected for crack propagation at intervals not to exceed 50 flight hours from initial crack detection.
(1) Cracks in the skin panel must not exceed 3 inches in length and must be limited to one crack per bay or one crack adjacent to and on either side of a horizontal member of the primary backup structure of the door.
(2) Cracks in the horizontal members of the primary backup structure which are parallel to and between the heel line and lightening holes must not exceed 2 inches in length, must be limited to one crack per horizontal member and adjacent horizontal members must be crackfree.
(c) If horizontal cracks are found during the inspection required by paragraph (a) of this AD which do not exceed the combined limitations noted in (c)(1) and (c)(2)below, the doors may remain in service provided the cracks are stop drilled and inspected for crack propagation at intervals not to exceed 50 flight hours from initial crack detection and the cabin pressure differential is limited to a maximum of 5.5 pounds per square inch for flight operations with cracks unrepaired.
(1) Cracks in the skin panel must not exceed 6 inches in length and must be limited to one crack per bay or one crack adjacent to and on either side of a horizontal member of the primary backup structure of the door.
(2) Cracks in the horizontal members of the primary backup structure are of the type and do not exceed the limitations of paragraph (b)(2) of this AD.
(d) Within 300 flight hours from the initial detection of a skin crack in excess of 3 inches in length, repair cracks in doors which are allowed to remain in service subject to the conditions in paragraphs (b) and (c) of this AD in accordance with sections 51-20-0 and 52-02-5 of the Structural Repair Manual for the Model, and thereafter continue to inspect the door in accordance with paragraph (a) of this AD at intervals not to exceed 800 flight hours time in service.
(e) If cracks are found during any of the inspections required by this AD that exceed the limitations specified in subparagraphs (b)(2) or (c)(1) of this AD, or are of a type which extend across the door frame, vertically across horizontal members, from a lightening hole to the heel line of the horizontal member, or between lightening holes, before further pressurized flight, repair the cracks in accordance with sections 51-20-0 and 52- 02-5 of the Structural Repair Manual for the Model and thereafter continue to inspect the door in accordance with paragraph (a) of this AD at intervals not to exceed 800 flight hours from the time of the repair.
(f) Upon incorporation of British Aircraft Corporation Modification 52-PM5448, compliance with this AD is no longer required.
(g) For the purpose of complying with this AD where number of landings has not been recorded, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing the total airplane flight hours by the operator fleet average time from takeoff to landing for the airplane type.
(h) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East 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 that operator.
NOTE: For additional clarification of types of cracking to be expected and crack limitations, refer to British Aircraft Corporation Alert Service Bulletin 52-A-PM5448, issue 2 (pages 1 and 2) dated July 4, 1977, and issue 1 (pages 3-5) dated March 16, 1977.
This amendment becomes effective May 15, 1978.
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74-26-02: 74-26-02 CONSOLIDATED AERONAUTICS: Amendment 39-2041. Applies to Colonial Model C-1, C-2 and Lake Model LA-4, LA-4A, LA-4P and LA-4-200 airplanes through serial number 599 certificated in all categories.
Compliance required as indicated.
To prevent loss of rudder control as a result of the failure of the arms of the rudder bellcrank assembly, P/N's 2-7109-1, 2-7103-91 and 1-7103-1, accomplish the following:
(a) Within 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 100 hours' time in service from the date of the last inspection except as provided in Paragraph (b) or until replaced in accordance with Paragraph (c):
Visually inspect the rudder bellcrank assembly, P/N's 2-7109-1, 2-7103-91 and 1-7103-1, in accordance with Lake Aircraft, Division of Consolidated Aeronautics, Inc. Service Letter L- 50, or later FAA approved revision.
(b) When rudder bellcrank assembly, P/N 2-7109-1 has arm P/N's 2-7109-23 and 2- 7109-24 installed or has arms of .080 inches or greater thickness installed, the inspection specified in paragraph (a) may be discontinued.
(c) Replace rudder bellcrank assemblies having cracked or deformed arms before further flight with a new rudder bellcrank assembly P/N 2-7109-1 having arms of .080 inches or greater thickness, or an equivalent part approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region.
(d) 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 Lake 4 Sales Corporation, P.O. Box 399, Tomball, Texas 77375. These documents may also be examined at the Office of Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C.
This amendment becomes effective December 27, 1974.
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93-24-06: 93-24-06 GENERAL DYNAMICS (CONVAIR): Amendment 39-8755. Docket 93-NM-44-AD.
Applicability: All Model 340, 440, and C-131B through C-131H (military) series airplanes, certificated in any category, including those airplanes modified for turbo-propeller power.
Compliance: Required as indicated, unless accomplished previously.
To prevent the loss of an elevator or rudder, resulting from installation of a suspected unapproved part, accomplish the following:
(a) Within 400 hours time-in-service or 180 days after the effective date of this AD, whichever occurs first, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of this AD.
(1) Remove the elevators and rudder in accordance with Parts 2.A.1. and 2.B.1., respectively, of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993; perform a detailed visual inspection of the elevator and rudder hinge pins and bushings to detect wear in accordance with the procedures described in Part 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21, 1990; and perform a detailed visual inspection of the elevator and rudder bearing plate assemblies to detect cracks and of the elevator and rudder bearings to detect chattering, looseness, dryness, or binding in accordance with Parts 2.A. and 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993.
(i) If any pin or bushing is worn, prior to further flight, replace the worn pin or bushing with a serviceable pin or bushing in accordance with the procedures described in Part 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21, 1990.
(ii) If any cracked bearing plate assembly is found, prior to further flight, replace the cracked bearing plate assembly with a serviceable bearing plate assembly in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993.
(iii) If any chattering, loose, dry, or seized bearing is found, prior to further flight, replace the discrepant bearing with a serviceable bearing in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993.
(2) Perform a hardness test to determine the equivalent strength of the elevator and rudder hinge pins and bushings in accordance with normal maintenance procedures. If the equivalent strength of any pin or bushing does not meet the type design strength specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable, prior to further flight, replace the discrepant pin or bushing with a serviceable pin or bushing in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993. Elevator and rudder hinge pins and bushings received directly from Convair that bear the Convair mark are excluded from the requirements of this paragraph. The Convair mark is an etched mark, which appears as follows:
CV
SD
The Convair mark is located on the top of the hinge pin and on the top of the bushing.
(i) For airplanes having pin assembly 240-2010908-1, the pins and bushings must meet type design strengths specified as follows:
Part
Part No.
Type Design
Strength
Pin
GD/Convair 240-2010904
170-195 ksi
Bushing
GD/Convair 240-2010903-7
120-145 ksi
(ii) For airplanes having pin assembly 240-2010908-3, the pins and bushings must meet type design strengths specified as follows:
Part
Part No.
Type Design
StrengthPin
GD/Convair 240-2010904
170-195 ksi
Bushing
GD/Convair 340-2015903
125-145 ksi
Bushing
Allison 9015192
120-145 ksi
(3) Reinstall the elevator and rudder, and ensure that proper mating of the pin and bushing tapered surfaces exists in accordance with Parts 2.A.5. and 2.B.5. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993.
(b) Repeat the requirements of paragraphs (a)(1) and (a)(3) of this AD at intervals not to exceed 2,000 hours time-in-service or 2 years, whichever occurs first, in accordance with Item 55-2-9 of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991.
NOTE 1: Paragraph (b) of this AD restates a requirement for repetitive actions contained in AD 92-06-06, Amendment 39-8186. Accomplishment of paragraphs (a)(1) and (a)(3) of this AD satisfies the corresponding requirements contained in AD 92-06-06.
(c) In accordance with the schedules specified in paragraphs (c)(1) and (c)(2) of this AD, report inspection results to the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California 90806-2425; fax (310) 988-5210. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.
(1) Within 72 hours after accomplishing the initial inspection required by paragraph (a) of this AD, report inspection results, positive or negative. A "positive" inspection result is defined as any finding of a discrepant part in the pin, bushing, or support structure.
(2) Within 72 hours after accomplishingany repetitive inspection required by paragraph (b) of this AD, report any positive inspection result.
(d) As of the effective date of this AD, no person shall install an elevator or rudder hinge pin or bushing on any airplane unless, prior to installation, the pin or bushing has been tested for hardness and meets the specified type design strength in accordance with paragraph (a)(2) of this AD, or unless the pin or bushing bears the Convair mark described in that paragraph.
(e) 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO.
(f) 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.
(g) The elevator/rudder removal and reinstallation, replacements, and inspections shall be done in accordance with General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21,1990; General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993; and General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991; as applicable. The incorporation by reference of General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21, 1990; and General Dynamics, Convair Division, Alert Service Bulletin 640(340D)S. B. No. A55-7, dated March 22, 1993; was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of April 22, 1992 (57 FR 9382, March 18, 1992). Copies may be obtained from General Dynamics, Convair Division, P.O. Box 85377, San Diego, California 92186-5377. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on January 18, 1994.
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