AD 92-08-13

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AD Number:
92-08-13
Document Type:
AD Final Rules
Docket Number:
91-NM-147-AD
Subject Heading:
Airworthiness Directives; BRITISH AEROSPACE Model ATP Series Airplanes
Subject:
Landing Gear Mechanism
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/02/1992
Make:
BAE Systems (Operations) Limited
Model:
ATP
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 92-08-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-NM-147-AD

AMENDMENT:   39-8224

AD NUMBER:   92-08-13

SUBJECT HEADING:   Airworthiness Directives; BRITISH AEROSPACE Model ATP Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 2, 1992.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
92-08-13 BRITISH AEROSPACE: Amendment 39-8224. Docket No. 91-NM-147-AD. Supersedes AD 90-21-11, Amendment 39-6806.
Applicability: Model ATP series airplanes, serial numbers 2001 through 2037, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent a gear-up landing, accomplish the following:

(a) Within 24 hours after November 29, 1990 (the effective date of AD 90-21-11, Amendment 39-6806), and thereafter at intervals not to exceed 30 hours time-in-service, perform an operational test of the hydraulic landing gear change-over valve mechanism, in accordance with British Aerospace Alert Service Bulletin A-ATP-32-26, Revision 1, dated September 25, 1990. Any binding or stiffness must be corrected prior to further flight, in accordance with instructions in the manufacturer's maintenance manual.

(b) Within 60 days after the effective date of this AD, modify the undercarriage emergency release mechanism and perform the associated functional test on the up lock release mechanism, in accordance with the accomplishment instructions in British Aerospace Service Bulletin ATP-32-29, Revision 1, dated June 6, 1991.

(c) Modification of the undercarriage emergency release mechanism, in accordance with British Aerospace Service Bulletin ATP-32-29, Revision 1, dated June 6, 1991, constitutes terminating action for the repetitive operational tests required by paragraph (a) of this AD.

(d) For airplanes having serial numbers 2001 through 2019, 2023 through 2027, 2030, 2031, and 2033: Within 60 days after the effective date of this AD, accomplish the following in accordance with British Aerospace Service Bulletin ATP-32-30, Revision 2, dated April 22, 1991; or Revision 3, dated May 20, 1991:

(1) Perform a one-time visual inspection of the swivel assembly in the landing gear normal selector mechanism teleflex cable to ensure that the correct connector is fitted. If the correct connector is not fitted, prior to further flight, install a connector and replacement teleflex cable.

(2) Install clevis pins, at specified locations, in lieu of bolts in the normal selector mechanism.

(3) Perform functional tests of the landing gear normal selector mechanism.

(e) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch.

(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 inspections, modifications, and repairs shall be done in accordance with British Aerospace Alert Service Bulletin A-ATP-32-26, Revision 1, dated September 25, 1990; British Aerospace Service Bulletin ATP-32-29, Revision 1, June 6, 1991; and British Aerospace Service Bulletin ATP-32-30, Revision 2, dated April 22, 1991, or Revision 3, dated May 20, 1991; which include the following list of effective pages:

Service Bulletin	Page Number	Revision Level	Date
			
A-ATP-32-26,	1, 3	1	September 25, 1990
Revision 1			
	2	Original	September 21, 1990
ATP-32-29,	1, 3, 7,	1	June 6, 1991
Revision 1	13		
			
	2, 4, 5, 6,	Original	March 27, 1991
	9, 11, 14		
			
	8, 10, 12	(not used)	
			
ATP-32-30,	1, 5, 11	2	April 22, 1991
Revision 2			
	2, 6	1	March 22, 1991
			
	3, 4, 7, 9	Original	March 14, 1991
			
	8, 10	(not used)	
			
ATP-32-30,	1	3	May 20, 1991
Revision 3			
	5, 11	2	April 22, 1991
			
	2, 6	1	March 22, 1991
			
	3, 4, 7, 9	Original	March 14, 1991
			
	8, 10	(not used)	

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, DC. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC.

(h) This amendment becomes effective on June 2, 1992.

FOOTER: