COMMONWEALTH OF AUSTRALIA
Civil Aviation Safety Regulations 1998 (CASR 1998)
CIVIL AVIATION SAFETY AUTHORITY
Regulation 39.001
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below issues the following
Airworthiness Directive (AD) under subregulation 39.001 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the
delegate considers necessary to correct an unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the
circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in
the compliance section.
CFM International Turbine Engines - CFM56 Series
AD/CFM56/33
Applicability:
Inspection of Fan Blades with
25 Degree Mid-span Shrouds
10/2014
This AD applies to CFM International (CFM) CFM56-3 turbofan engines, all serial
numbers, when equipped with fan blades with 25 degree mid-span shrouds: Part
Numbers (P/N) 9527M99P08, 9527M99P09, 9527M99P10, 9527M99P11, and
1285M39P01, or fan blade pairs P/N 335-088-901-0, 335-088-902-0, 335-088-903-0,
and 335-088-904-0.
Note 1: These engines are known to be installed on, but not limited to, Boeing 737
series aeroplanes.
Note 2: The installation of fan blades with 25 degree mid-span shrouds is not allowed
on the CFM56-3C engine model.
Requirements:
1.
INSPECTION
Perform an inspection of fan blades P/N 9527M99P08, 9527M99P09,
9527M99P10, 9527M99P11, and 1285M39P01, or fan blade pairs
P/N 335-088-901-0, 335-088-902-0, 335-088-903-0, and 335-088-904-0 in
accordance with paragraphs 3.A (On-wing) or 3.B (In-shop) of CFM Service
Bulletin (SB) CFM56-3/3B/3C 72-1067 original issue.
Note 3: Inspections completed in accordance with CFM SB CFM56-3/3B/3C
S/B 72-1067 original issue, within the last 3,000 Flight Cycles (FC) before the
effective date of this AD satisfies Requirement 1 of this AD.
2.
If any damage is found, remove and replace the blades as instructed in the
accomplishment instructions of CFM SB CFM56-3/3B/3C 72-1067 original
issue.
3.
Do not install on any CFM56-3 engine model fan blades P/N 9527M99P08,
9527M99P09, 9527M99P10, 9527M99P11, and 1285M39P01, or fan blade pairs
P/N 335-088-901-0, 335-088-902-0, 335-088-903-0, and 335-088-904-0 unless
they have been previously inspected in accordance with paragraph 3 of the
accomplishment instructions of CFM SB CFM56-3/3B/3C 72-1067 original
issue.
Note 4: The use of later approved revisions of CFM SB CFM56-3/3B/3C 72-1067
original issue is acceptable for compliance with the requirements of this AD.
Note 5: EASA AD 2009-0036 dated 20 February 2009 refers.
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Federal Register of Legislative Instruments F2014L00502
COMMONWEALTH OF AUSTRALIA
Civil Aviation Safety Regulations 1998 (CASR 1998)
CIVIL AVIATION SAFETY AUTHORITY
Regulation 39.001
CFM International Turbine Engines - CFM56 Series
AD/CFM56/33 (continued)
Compliance:
1, 2 and 3. The actions in Requirements 1, 2 and 3 must be taken as follows:
(a) for Requirement 1: if not previously complied with, before further flight.
Otherwise, at intervals not exceeding 3,000 FC from the last inspection.
(b) for Requirement 2: before further flight.
(c) for Requirement 3: after the effective date of this AD.
This Airworthiness Directive becomes effective on 9 May 2014.
Background:
The requirements of this AD address the same unsafe condition as EASA
AD 2009-0036 with an effective date of 20 February 2009.
A multiple fan blade failure event was reported on a CFM56-3 engine model. Severe
wear was observed on the underside of the fan blade platforms at the contact location
with the fan blade dampers. This resulted in poor damping of the fan blade set and
contributed to high dynamic stress of the blades.
For the reasons stated above, this AD requires repetitive inspections of fan blades
with 25 degrees mid-span shrouds as defined by CFM SB CFM56-3/3B/3C 72-1067
original issue in order to reduce the risk of a multiple fan blade failure event which
could result in an uncontained engine rotor failure.
Mike Higgins
Delegate of the Civil Aviation Safety Authority
30 April 2014
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Federal Register of Legislative Instruments F2014L00502