80-15-51 PRATT & WHITNEY AIRCRAFT: Amendment 39-3898. Applies to JT8D-1, -1A, -1B, -5, -7, -7A, -7B, -9, -9A, -11, -15, -17, -17R, -209, and -209A model turbofan engines.
Compliance is required as indicated.
To prevent uncontained failure of engine rear compressor front hubs, accomplish the following:
Inspect, in accordance with the following schedule, unless already accomplished, all eighth stage rear compressor front hubs, P/Ns 690908, 701308, 717608, 717708, and 738308, which contain balance cuts, for cracks in accordance with the ultrasonic or fluorescent magnetic particle procedures contained in Pratt & Whitney Aircraft Alert Service Bulletin ASB 5154, Revision No. 1, dated July 16, 1980, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region:
ENGINE MODEL
HUB TOTAL CYCLES
AS OF JULY 21, 1980
INSPECTION REQUIRED
JT8D-1, -1A, -1B,
-5, -7, -7A, and -7B
A) Less than 13,000.
A) Before accumulation of 15,000 cycles.
B) Within the next 2,000 than 15,000.
B) 13,000 or more and less cycles.
C) 15,000 or more.
C) Before accumulation of 17,000 cycles or within the next 500 cycles, whichever is later.
JT8D-9, -9A, -11, -15, -209, and -209A
A) Less than 10,000.
A) Before accumulation of 12,000 cycles.
B) 10,000 or more and less than 12,000.
B) Within the next 2,000 cycles.
C) 12,000 or more and less than 14,000.
C) Before accumulation of 14,000 cycles or within the next 500 cycles, whichever is later.
D) 14,000 or more and less than 15,000.
D) Within the next 500 cycles.
E) 15,000 or more and less than 16,000.
E) Within the next 300 cycles.
F) 16,000 or more.
F) Within the next 200 cycles.
JT8D-17 and -17R
A) Less than 11,000.
A) Before accumulation of 12,000 cycles.
B) 11,000 or more and less than 12,000.
B) Within the next 1,000 cycles.
C) 12,000 or more and less than 13,000.
C) Before accumulation of 13,000 cycles or within the next 500 cycles, whichever is later.
D) 13,000 or more and less than 13,500.
D) Within the next 500 cycles.
E) 13,500 or more and less than 14,000.
E) Before accumulation of 14,000 cycles or within the next 100 cycles, whichever is later.
F) 14,000 or more.
F) Within the next 100 cycles, unless already accomplished.
All models
Inspect thereafter at intervals not to exceed 6,000 cycles in service since last inspection.
(NOTE: Established life limits are not to be exceeded.)
Remove from service, before further flight, any rear compressor front hub having a crack indication.
Report defects found to Chief, Engineering and Manufacturing Branch, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, within 5 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) Airplanes may be ferried in accordance with the provisions of FAR 21.197 to a base where the AD can be accomplished. Upon request of the operator an equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region.
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 Pratt & Whitney Aircraft, East Hartford, Connecticut 06108. These documents may also be examined at FAA, 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 AD is maintained by the FAA at its headquarters in Washington, D.C., and at the FAA, New England Region Headquarters, Burlington, Massachusetts.
This AD supersedes AD T80-14-51 issued July 3, 1980.
This Amendment 39-3898 becomes effective August 21, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram of July 16, 1980.