AD 96-13-08

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AD Number:
96-13-08
Document Type:
AD Final Rules
Docket Number:
96-ANE-10
Subject Heading:
PRATT & WHITNEY Models PW4000 Series Engines
Subject:
AFT Cascade Support Frame Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/01/1996
Make:
Pratt & Whitney Division
Model:
PW4050 | PW4052 | PW4056 | PW4060 | PW4060A | PW4060C | PW4062 | PW4152 | PW4156 | PW4156A | PW4158 ...Show more
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 96-13-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   96-ANE-10

AMENDMENT:   39-9676

AD NUMBER:   96-13-08

SUBJECT HEADING:   PRATT & WHITNEY Models PW4000 Series Engines

ACTION:  

SUMMARY:  

DATES:   Effective August 1, 1996.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   96-13-08 PRATT & WHITNEY: Amendment 39-9676. Docket 96-ANE-10.
Applicability: Pratt & Whitney (PW) PW4000 series turbofan engines, with thrust reverser, Supplemental Type Certificate (STC) No. SJ514NE, installed on Airbus A300-600 and A310 series aircraft, and thrust reverser, STC No. SE744NE, installed on McDonnell Douglas MD-11 series aircraft. These thrust reversers incorporate aft cascade support frame assemblies, Part Numbers (P/N's) 221-0516-503 and 221-0516-504. NOTE: This airworthiness directive (AD) applies to each engine with affected thrust reversers identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines with affected thrust reversers that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine with affected thrust reversers from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent aft cascade support frame assembly failure due to cracks, which can result in thrust reverser hardware liberation and ejection from the aircraft during thrust reverser operation, which can contaminate the runway with debris, causing an operational hazard to other aircraft during takeoff and landing, accomplish the following:
(a) For engines with affected thrust reversers installed on Airbus A300-600 and A310 series aircraft, accomplish the following:
(1) Initially inspect aft cascade support frame assemblies for cracks within 250 flight hours after the effective date of this AD, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW Service Bulletin (SB) No. PW4NAC 78-78, Revision 6, dated March 6, 1996.
(2) Thereafter, inspect aft cascade support frame assemblies for cracks at intervals not to exceed 450 flight hours since the last inspection, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4NAC 78-78, Revision 6, dated March 6, 1996.
(3) For aft cascade support frame assemblies that do not meet the return to service criteria stated in the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4NAC 78-78, Revision 6, dated March 6, 1996, prior to further flight, accomplish either of the following:
(i) Remove from service cracked aft cascade support frame assemblies, and replace with a serviceable part; or
(ii) Lockout the thrust reverser in accordance with the Airbus A300- 600 and A310 series Aircraft Maintenance Manuals, as applicable, for a time period not to exceed 10 days. At the conclusion of the 10-day lockout period, prior to further flight remove any cracked aft cascade support frame assemblies and replace with serviceable parts.
(b) For engines with affected thrust reversers installed on McDonnell Douglas MD- 11 series aircraft, accomplish the following:
(1) Initially inspect aft cascade support frame assemblies for cracks within 250 flight hours after the effective date of this AD, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996.
(2) Thereafter, inspect aft cascade support frame assemblies for cracks at intervals not to exceed 450 flight hours since the last inspection, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996.
(3) For aft cascade support frame assemblies that do not meet the return to service criteria stated in the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996, prior to further flight, accomplish either of the following:
(i) Remove from service cracked aft cascade support frame assemblies, and replace with a serviceable part; or
(ii) Lockout the thrust reverser in accordance with the McDonnell Douglas MD-11 series Aircraft Maintenance Manual, for a time period not to exceed 10 days. At the conclusion of the 10-day lockout period, prior to further flight remove any cracked aft cascade support frame assemblies and replace with serviceable parts.
(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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance with the following PW SB's:

Document No.	Pages	Revision	Date
PW4NAC 78-78	1	6	March 6, 1996
	2,3	2	October 31, 1995
	4-6	6	March 6, 1996
	7	5	October 31, 1995
	8-11	6	March 6, 1996
	12	5	October 31, 1995
	13-19	6	March 6, 1996
	20-22	5	October 31, 1995
	23-34	6	March 6, 1996
	35	5	October 31, 1995
	36,37	6	March 6, 1996
	38	5	October 31, 1995
	39,40	6	March 6, 1996
Total pages: 40.			
PW4MD11 78-67	1-38	5	March 6, 1996
Total pages: 38.			

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 Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-4503. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment becomes effective on August 1, 1996.

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