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ADs updated daily at www.Tdata.com
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| 2019-22-05 |
GENERAL ELECTRIC COMPANY: Amendment 39-19784; Docket No. FAA-2019-0394; Product Identifier 2017-NE-36-AD. |
(a) EFFECTIVE DATE
This AD is effective December 23, 2019.
(b) AFFECTED ADS
This AD replaces AD 2017-23-06, Amendment 39-19100 (82 FR 52830,
November 15, 2017).
(c) APPLICABILITY
This AD applies to all General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, and CF34-8C5A3 model turbofan
engines.
(d) SUBJECT
Joint Aircraft System Component (JASC) Code 7531, Compressor bleed
governor.
(e) UNSAFE CONDITION
This AD was prompted by multiple engine fires that have occurred as a
result of malfunctions related to the operability bleed valve (OBV).
The FAA is issuing this AD to prevent failure of the OBV. The unsafe
condition, if not addressed, could result in engine fire and damage to
the airplane.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless
already done.
(g) REQUIRED ACTIONS
(1) For CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 model turbofan
engines with serial numbers (S/Ns): 965101 through 965670 inclusive;
194101 through 194999 inclusive; and 195101 through 195653 inclusive:
(i) Perform an inspection of the OBV bleed air manifold link rod assem-
blies and the OBV fuel fittings within 500 flight hours after November
30, 2017 (effective date of AD 2017-23-06) or before next flight after
the effective date of this AD, whichever occurs later.
(ii) Within 880 flight hours since the previous inspection, 500 flight
hours from the effective date of this AD, or 6,880 flight hours since
new, whichever occurs later, inspect the OBV bleed air manifold link
rod assemblies, the OBV fuel fittings, and the OBV fuel tubes.
(iii) Thereafter, perform additional repeat inspections of the OBV bleed
air manifold link rod assemblies, the OBV fuel fittings, and the OBV
fuel tubes within every 880 flight hours since the previous
inspection.
(iv) Use the Accomplishment Instructions, Paragraph 3.B. of GE CF34-8C S/B
75-0020, R04, dated May 10, 2019 ("the SB"), to perform the inspec-
tions in paragraphs (g)(1)(i) through (iii) of this AD and, per the
criteria for the results of inspections in Paragraph 3.B. of the SB,
do the following:
(A) Replace any OBV or fuel tube that is leaking and tighten or replace
any loose OBV fuel tube clamps with a part eligible for installation
before further flight.
(B) Replace any worn OBV link rod assembly hardware within 50 flight
cycles after the inspection required by paragraphs (g)(1)(i), (ii), or
(iii) of this AD. The engine can be returned to service each day for
up to the 50 flight cycles if the OBV fittings are inspected each day
for fuel leaks and looseness and, if they do not require removal based
on the criteria in Table 1, "OBV Inspection," of GE SB CF34-8C S/B 75
-0020, R04, dated May 10, 2019.
(2) For CF34-8C5B1 model turbofan engines with S/Ns not listed in para-
graph (g)(1) of this AD and for all CF34-8C5A2 and CF34-8C5A3 model
turbofan engines, perform the following:
(i) For engines with 6,000 flight hours or more since new on the effective
date of this AD, perform an initial inspection of the OBV bleed air
manifold link rod assemblies, OBV fuel fittings, and OBV fuel tubes
within 880 flight hours after the effective date of this AD.
(ii) For engines with less than 6,000 flight hours since new on the effec-
tive date of this AD, perform an initial inspection of the OBV bleed
air manifold link rod assemblies, OBV fuel fittings, and OBV fuel
tubes within 880 flight hours time in service or 6,880 flight hours
since new, whichever occurs later.
(iii) Thereafter, repeat the inspection of the OBV bleed air manifold link
rod assemblies, OBV fuel fittings, and OBV fuel tubes within 880
flight hours since the last inspection.
(iv) Use the Accomplishment Instructions, Paragraph 3.B. of GE CF34-8C S/B
75-0020, R04, dated May 10, 2019, to perform the inspections in para-
graphs (g)(2)(i) through (iii) of this AD.
(v) Replace any parts according to the criteria in paragraph (g)(1)(iv) of
this AD after the inspection required by paragraphs (g)(2)(i), (ii) or
(iii) of this AD.
(3) For all affected engines, the reporting instructions in GE SB CF34-8C
S/B 75-0020, R04, dated May 10, 2019, are not required by this AD.
(h) CREDIT FOR PREVIOUS ACTIONS
(1) For engines identified in paragraph (g)(1) of this AD, you may take
credit for the inspection of the OBV bleed air manifold link rod
assemblies and the OBV fuel fittings required by paragraph (g)(1)(i)
of this AD if you performed this inspection before November 30, 2017
(the effective date of AD 2017-23-06) using GE SB CF34-8C SB 75-0019,
Revision 01, dated October 24, 2017, or R00, dated August 4, 2017.
(2) For all affected engines, you may take credit for the inspection of
the OBV bleed air manifold link rod assemblies and the OBV fuel fit-
tings required by paragraph (g)(1)(i) or (g)(2)(i) of this AD if you
performed this inspection before the effective date of this AD using
GE SB CF34-8C SB 75-0020, Revision 03, dated December 14, 2018.
(3) You are still required to perform the repeat inspections and any re-
placements, as needed, required by paragraphs (g)(1)(ii) through (g)
(1)(iv) of this AD.
(i) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)
(1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your request to your principal
inspector or local Flight Standards District Office, as appropriate.
If sending information directly to the manager of the certification
office, send it to the attention of the person identified in paragraph
(j) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal in-
spector, or lacking a principal inspector, the manager of the local
flight standards district office/certificate holding district office.
(j) RELATED INFORMATION
For more information about this AD, contact Michael Richardson-Bach,
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington,
MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: michael.
richardson-bach@faa.gov.
(k) MATERIAL INCORPORATED BY REFERENCE
(1) The Director of the Federal Register approved the incorporation by
reference (IBR) of the service information listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) General Electric Company (GE) Service Bulletin CF34-8C SB 75-0020, R04
dated May 10, 2019.
(ii) [Reserved]
(3) For GE service information identified in this AD, contact General
Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH
45215, phone: 513-552-3272; fax: 513-552-3329; email: geae.aoc@ge.com.
(4) You may view this service information at FAA, Engine and Propeller
Standards Branch, 1200 District Avenue, Burlington, MA 01803. For in-
formation on the availability of this material at the FAA, call 781-
238-7759.
(5) You may view this service information at the National Archives and
Records Administration (NARA). For information on the availability of
this material at NARA, email: fedreg.legal@nara.gov, or go to: https:
//www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on November 6, 2019. Robert J. Ganley
Manager, Engine and Propeller Standards Branch, Aircraft Certification
Service.
FOR FURTHER INFORMATION CONTACT: Michael Richardson-Bach, Aerospace Engi-
neer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone:
781-238-7747; fax: 781-238-7199; email: michael.richardson-bach@faa.gov.
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