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Inspection, and
Sub Task 72–53–02–250–051 Eddy Current Inspection,
Rim Bolt Holes, and
Sub Task 72–53–02–250–054 Eddy Current Inspection,
Disk Bore Area.
HPT Disk, Stage 2 ..................................................... All ....................................... Sub Task 72–53–06–230–051 Fluorescent-Penetrant
Inspection, and
Sub Task 72–53–06–250–051 Eddy Current Inspection,
RimBolt Holes, and
Sub Task 72–53–06–250–054 Eddy Current Inspection,
Disk Bore Area.
LPT Rotor Shaft ......................................................... All ....................................... Sub Task 72–55–01–240–051 Magnetic Particle Inspect.
LPT Disks, Stages 1–5 .............................................. All ....................................... Sub Task 72–57–02–230–051 Fluorescent-Penetrant
Inspect.
LPT Rotor Torque Cone ............................................ All ....................................... Sub Task 72–57–03–220–051 Fluorescent-Penetrant
Inspect.
For CF6–80E1 Engines configured with the R88DT Turbine:
Disk Shaft, HPT Rotor Stage 1 (R88DT, No Rim
Bolt Holes).
All ....................................... Sub Task 72–53–16–230–052 Fluorescent-Penetrant
Inspect, and
Sub Task 72–53–16–250–XXX Disk Bore Area Eddy
Current Inspection.
Disk, HPT Rotor Stage 2 (R88DT, No Rim Bolt
Holes).
All ....................................... Sub Task 72–53–18–230–051 Fluorescent-Penetrant
Inspect, and
Sub Task 72–53–18–250–XXX Disk Bore Area Eddy
Current Inspection.
HPT Rotor Rotating Interstage Seal (R88DT) ........... All ....................................... Sub Task 72–53–17–230–051 Fluorescent-Penetrant
Inspect, and
Sub Task 72–53–17–250–XXX Seal Bore Area Eddy
Current.
HPT Rotor Forward Outer Seal (R88DT) .................. All ....................................... Sub Task 72–53–21–230–051 Fluorescent-Penetrant
Inspect, and
Sub Task 72–53–21–250–XXX Seal Bore Area Eddy
Current.
(2) For the purposes of these mandatory
inspections, piece-part opportunity means:
(i) The part is considered completely
disassembled when accomplished in
accordance with the disassembly instructions
in the manufacturer’s engine manual; and
(ii) The part has accumulated more than
100 cycles-in-service since the last piece-part
opportunity inspection, provided that the
part was not damaged or related to the cause
for its removal from the engine.’’
(b) Except as provided in paragraph (c) of
this AD, and notwithstanding contrary
provisions in section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these
mandatory inspections shall be performed
only in accordance with the Life Limits
Section of the manufacturer’s ICA.
Alternative Methods of Compliance
(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 Engine Certification
Office (ECO). Operators must submit their
requests through an appropriate FAA
Principal Maintenance Inspector (PMI), who
may add comments and then send it to the
ECO.
Note 2: Information concerning the
existence of approved alternative methods of
compliance with this airworthiness directive,
if any, may be obtained from the ECO.
Continuous Airworthiness Maintenance
Program
(d) FAA-certificated air carriers that have
an approved continuous airworthiness
maintenance program in accordance with the
record keeping requirement of § 121.369 (c)
of the Federal Aviation Regulations [14 CFR
121.369 (c)] of this chapter must maintain
records of the mandatory inspections that
result from revising the Life Limits Section
of the Instructions for Continuous
Airworthiness (ICA) and the air carrier’s
continuous airworthiness program.
Alternately, certificated air carriers may
establish an approved system of record
retention that provides a method for
preservation and retrieval of the maintenance
records that include the inspections resulting
from this AD, and include the policy and
procedures for implementing this alternate
method in the air carrier’s maintenance
manual required by § 121.369 (c) of the
　
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