AIRWORTHINESS
DIRECTIVE
CAA-AD-075/2002
Supersedes CAA-AD-060/2000
Date of issue: July 22, 2002
ENGINE - ROTATING ENGINE PART - INSPECTION
Applicability: This airworthiness
directive (AD) is applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3,
-3B, -3C, -5, -5B, -5C, and -7B series turbofan engines, installed on but not
limited to McDonnell Douglas DC-8 series, Boeing 737 series, Airbus Industrie
A319, A320, A321, and A340 series, as well as Boeing C-135, E-3, E-6, KC-135,
KE-3, and RC-135 (military) series airplanes.
Effective date: August 01, 2002
Compliance: Required as indicated in FAA AD 2002-13-03.
Remarks: The compliance of this AD must be recorded
in Aircraft Logbook, where applicable the requirements of this AD must be
integrated into Aircraft Technical Documentation. Address inquiries concerning
this AD to: Civil Aviation Authority, Airworthiness Division, Ruzyne Airport,
160 08 Prague 6, Czech Republic, tel.: 420 2 33320922, fax: 420 2 20562270.
Ing. Pavel MATOUŠEK
Director of Airworthiness Division
CAA CZ
2002-13-03 CFM
International: Amendment
39-12790. Docket No. 98-ANE-38-AD. Supersedes AD 2000-12-01, Amendment
39-11779.
Applicability
This airworthiness directive (AD) is applicable to CFM International (CFMI)
CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C, and -7B series turbofan engines,
installed on but not limited to McDonnell Douglas DC-8 series, Boeing 737
series, Airbus Industrie A319, A320, A321, and A340 series, as well as Boeing
C-135, E-3, E-6, KC-135, KE-3, and RC-135 (military) series airplanes.
Note 1: This AD applies to each engine 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
that have been modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request approval
for an alternative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by this
AD; and, if the unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.
Compliance
Compliance with this AD is required as indicated, unless already accomplished.
To prevent critical life-limited rotating engine part failure, which could
result in an uncontained engine failure and damage to the airplane, accomplish
the following:
Inspections
(a) Within the next 30 days after the effective date of this AD, revise the
Airworthiness Limitations Section (chapter 05-00-00) of Engine Shop Manual
(ESM) CFMI-TP.SM.4, for CFM56-2 series engines, ESM CFMI-TP.SM.6, for
CFM56-2A/-2B series engines, ESM CFMI-TP.SM.5, for CFM56-3/-3B/-3C series
engines, ESM CFMI-TP.SM.7 for CFM56-5 series engines, ESM CFMI-TP.SM.9 for
CFM56-5B series engines, ESM CFMI-TP.SM.8 for CFM56-5C series engines, and ESM
CFMI-TP.SM.10 for CFM56-7B series engines, and for air carrier operations,
revise the approved continuous airworthiness maintenance program, by adding the
following:
"MANDATORY INSPECTIONS
(1) Perform inspections of the following parts at each piece-part opportunity
in accordance with the Inspection/Check section instructions provided in the
applicable manual sections listed below:
|
Engine models |
Part name |
Engine manual section |
Inspection |
|
All
Models |
Fan Disk
(All Part Numbers (P/N)) |
72-21-03 |
Disk
Fluorescent Penetrant Inspection (FPI) and |
|
All
Models |
Fan Shaft
(All P/N) |
72-22-01 |
Magnetic Particle
Inspection (MPI). |
|
CFM56-2,
-2A, -2B, -3, -3B, |
HPT Disk
(All P/N) |
72-52-02 |
FPI, Disk
Bore ECI and Disk Rim Bolt Hole(s) ECI. |
|
CFM56-5,-5B,
-5C, and -7B |
HPT Disk
(All P/N) |
72-52-02 |
FPI, Disk
Bore ECI. |
|
CFM56-2 |
HPT Front
Rotating Air Seal (All P/N) |
72-52-03 |
FPI, Seal
Bore ECI and Bolt Hole(s) or Focused FPI as applicable. |
|
CFM56-2A,
-2B, -3, -3B, and |
HPT Front
Rotating Air Seal (All P/N) |
72-52-03 |
FPI, Seal
Bore ECI and Bolt Hole(s) ECI. |
|
CFM56-5,
-5B, -5C, and -7B |
HPT Front
Rotating Air Seal (All P/N) |
72-52-03 |
FPI, Seal
Bore ECI and Bolt Hole(s) Focused FPI. |
|
All
Models |
HPC Stage
1-2 Spool (All P/N) |
72-31-04 |
FPI. |
|
All
Models |
HPC Stage
3 Disk (All P/N) |
72-31-05 |
FPI. |
|
All
Models |
HPC Stage
4-9 Spool (All P/N) |
72-31-06 |
FPI. |
|
All
Models |
HPC Front
Shaft (All P/N) |
72-31-07 |
FPI |
|
All
Models |
HPC Rear
(CDP) Air Seal (All P/N) |
72-31-08 |
FPI. |
|
All
Models |
LPT Stage
1 Disk (All P/N) |
72-54-03 |
FPI. |
|
All
Models |
LPT Stage
2 Disk (All P/N) |
72-54-03 |
FPI. |
|
All
Models |
LPT Stage
3 Disk (All P/N) |
72-54-03 |
FPI |
|
All
Models |
LPT Stage
4 Disk (All P/N) |
72-54-03 |
FPI. |
|
CFM56-5C |
LPT Stage
5 Disk (All P/N) |
72-54-03 |
FPI. |
|
All
Models |
LPT Rotor
Support (All P/N) |
72-54-05 |
FPI. |
|
All
Models |
LPT Shaft
(All P/N) |
72-55-01 |
MPI. |
|
CFM56-2,
-2A, -2B, -3, -3B |
LPT Stub
Shaft (All P/N) |
72-55-02 |
FPI. |
(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 Sec. 43.16 of the Federal Aviation Regulations (14 CFR
43.16), these mandatory inspections must be performed only in accordance with
the Time Limits section of the manufacturer's ESM.
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
Manager, Engine Certification Office. Operators must submit their request
through an appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Engine Certification Office.
Note 2: Information concerning the existence of approved alternative
methods of compliance with this airworthiness directive, if any, may be
obtained from the Engine Certification Office.
Special Flight Permits
(d) Special flight permits may be issued in accordance with §
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate the airplane to a location where the requirements of this AD
can be accomplished.
Continuous Airworthiness Maintenance Program
(e) FAA-certificated air carriers that have an approved continuous
airworthiness maintenance program in accordance with the record keeping
requirement of Sec. 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 Airworthiness Limitations Section of the
applicable ESM and the air carrier's continuous airworthiness program.
Alternatively, 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 Sec. 121.369(c) of the Federal
Aviation Regulations (14 CFR 121.369 (c)); however, the alternate system must
be accepted by the appropriate PMI and require the maintenance records be
maintained either indefinitely or until the work is repeated. Records of the
piece-part inspections are not required under Sec. 121.380(a)(2)(vi) of the
Federal Aviation Regulations (14 CFR 121.380(a)(2)(vi)). All other operators
must maintain the records of mandatory inspections required by the applicable
regulations governing their operations.
Note 3: The requirements of this AD have been met when the ESM changes
are made and air carriers have modified their continuous airworthiness
maintenance plans to reflect the requirements in the applicable ESM.
Effective Date
(f) This amendment becomes effective on August 1, 2002.