Tdata AD

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PROPOSED AD	GENERAL ELECTRIC COMPANY: Docket No. FAA-2019-0394; Product Identifier 2017-NE-36-AD.

(a) COMMENTS DUE DATE

    The FAA must receive comments on this AD action by August 12, 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
    assemblies 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 inspec-
      tion.

(iv) Use the Accomplishment Instructions, Paragraph 3.B., of GE CF34-8C-AL
     S/B 75-0020, R04,  dated May 10, 2019 ("the SB"),  to perform the in-
     spections 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),
    (g)(1)(ii), or (g)(1)(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-AL 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 flights hours 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  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-AL
     S/B 75-0020, R04,  dated May 10, 2019,  to perform the inspections in
     paragraphs (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), (g)(2)
    (ii), or (g)(2)(iii) of this AD.

(3) For all affected engines, the reporting instructions in GE SB CF34-8C-
    AL 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
    fittings 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 in-
    spector 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

(1) 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.

(2) For 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.  You
    may view this service information  at  the  FAA,  Engine and Propeller
    Standards Branch,  1200 District Avenue, Burlington, MA.  For informa-
    tion on the availability of this material  at  the  FAA, call 781-238-
    7125.

Issued in Burlington, Massachusetts,  on June 24, 2019.  Robert J. Ganley,
Manager,  Engine and Propeller  Standards  Branch,  Aircraft Certification
Service.

DATES: The FAA must receive comments  on this proposed  AD  by  August 12,
2019.

PREAMBLE

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0394; Product Identifier 2017-NE-36-AD]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Turbofan
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2017-23-06, which applies to certain General Electric Company (GE)
CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 engines. AD 2017-23-06
requires an inspection of the bleed air manifold link rod assemblies
and the supply, return, and drain fuel fittings on the operability
bleed valve (OBV). Since the FAA issued AD 2017-23-06, the manufacturer
developed improved inspection techniques and determined these
inspections should be applied to additional engine models. This
proposed AD would require repetitive inspections of the OBV fuel tubes,
OBV bleed air manifold link rod assemblies, and the OBV fuel fittings
and replacement of OBVs or related hardware that fail inspection. The
FAA is proposing this AD to address the unsafe condition on these
products.

DATES: The FAA must receive comments on this proposed AD by August 12,
2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:

Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the
instructions for submitting comments.

Fax: 202-493-2251.

Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.

Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, 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.
You may view this service information at the FAA, Engine and Propeller
Standards Branch, 1200 District Avenue, Burlington, MA. For information
on the availability of this material at the FAA, call 781-238-7125.

Examining the AD Docket

You may examine the AD docket on the internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2019-0394;
or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION 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.

SUPPLEMENTARY INFORMATION:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include "Docket No. FAA-2019-0394;
Product Identifier 2017-NE-36-AD" at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.

The FAA will post all comments, without change, to http://www.regulations.
gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact we receive about this proposed AD.

Discussion

The FAA issued AD 2017-23-06, Amendment 39-19100 (82 FR 52830,
November 15, 2017), ("AD 2017-23-06"), for certain General Electric
Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 engines. AD
2017-23-06 requires an inspection of the bleed air manifold link rod
assemblies and the supply, return, and drain fuel fittings on the OBV.
AD 2017-23-06 resulted from reports that significant fuel leaks, some
resulting in engine fires, occurred on multiple occasions due to
malfunctions related to the OBVs. The FAA issued AD 2017-23-06 to
address the unsafe condition on these products.

Actions Since AD 2017-23-06 Was Issued

Since the FAA issued AD 2017-23-06, the manufacturer has developed
improved inspections of the OBV bleed air manifold link rod assemblies
and OBV fuel fittings, added an inspection of the OBV fuel tubes, and
determined that these inspections should be applied to additional
engine models. GE published these improved inspections in GE Service
Bulletin (SB) CF34-8C-AL S/B 75-0020, R04, dated May 10, 2019.

Related Service Information Under 1 CFR Part 51

The FAA reviewed GE SB CF34-8C-AL S/B 75-0020, R04, dated May 10,
2019. The SB describes procedures for inspecting the bleed air manifold
link rod assemblies; the supply, return, and drain fuel fittings; and
the fuel tubes on the OBV. This service information is reasonably
available because the interested parties have access to it through
their normal course of business or by the means identified in the
ADDRESSES section.

FAA's Determination

The FAA is proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

This proposed AD would retain all the requirements of AD 2017-23-06.
This proposed AD would revise the inspections of the OBV bleed air
manifold link rod assemblies and OBV fuel fittings and require
inspections of the OBV fuel tubes. In addition, this proposed AD would
expand the applicability of these inspections to include additional GE
CF34-8C model turbofan engines.

Interim Action

The FAA considers this proposed AD interim action. The FAA will
consider further rulemaking based on the continued investigation and
development of corrective action by the manufacturer.

Costs of Compliance

The FAA estimates that this proposed AD affects 1,297 engines installed
on airplanes of U.S. registry.

The FAA estimates the following costs to comply with this proposed AD:

Estimated Costs

Action	Labor cost	Parts cost	Cost per product	Cost on U.S. operators
Inspection of OBV fuel tubes, assemblies, and fittings.	1 work-hour x $85 per hour = $85	$0	$85	$110,245

The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspection. The FAA has no way of determining the number of
aircraft that might need these replacements:

On-Condition Costs

Action	Labor cost	Parts cost	Cost per product
Replace OBV	2 work-hours x $85 per hour = $170	$17,230	$17,400
Replace OBV support hardware	2.25 work-hours x $85 per hour = $191.25	3,595	3,786.25

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.

The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, "General
requirements." Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.

Regulatory Findings

The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.

For the reasons discussed above, I certify that the proposed
regulation:

(1) Is not a "significant regulatory action" under Executive
Order 12866,

(2) Will not affect intrastate aviation in Alaska, and

(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2017-23-06, Amendment 39-19100 (82 FR 52830, November 15, 2017), and
adding the following new AD: