[Federal Register Volume 62, Number 5 (Wednesday, January 8, 1997)]
[Rules and Regulations]
[Pages 1039-1041]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-474]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-ANE-06; Amendment 39-9864; AD 96-26-01]
RIN 2120-AA64
Airworthiness Directives; General Electric Aircraft Engines CT7
Series Turboprop Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to General Electric Aircraft Engines (GE) CT7 series
turboprop engines, that requires replacement of the gas generator
turbine stage 2 forward cooling plates prior to the published cyclic
life limits. The AD also defines the new, reduced cyclic life limits
for the affected forward cooling plates. This amendment is prompted by
reports of gas generator turbine stage 2 forward
[[Page 1040]]
cooling plate failures. The actions specified by this AD are intended
to prevent gas generator turbine stage 2 forward cooling plate failure,
which could result in an uncontained engine failure.
DATES: Effective March 10, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 10, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from GE Aircraft Engines, 1000 Western Ave., Lynn, MA 01910;
telephone (617) 594-3140, fax (617) 594-4805. This information may be
examined at the Federal Aviation Administration (FAA), New England
Region, Office of the Assistant Chief Counsel, 12 New England Executive
Park, Burlington, MA; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dave Keenan, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7139, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to General Electric Aircraft Engines
(GE) CT7 series turboprop engines was published in the Federal Register
on September 17, 1996 (61 FR 48866). That action proposed to require
replacement of the gas generator turbine stage 2 forward cooling plate
within 30 days after the effective date of the AD, or prior to reaching
the new, reduced cyclic life limits listed in the Accomplishment
Instructions of GE Aircraft Engines (CT7-TP Series) SB A72-381, dated
January 17, 1996, whichever occurs later.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public.
The FAA has determined that an additional paragraph (e) is
necessary to fully implement the new life limits for gas generator
turbine (GGT) stage 2 forward cooling plates, Part Number (P/N)
60604T10P01 and P/N 5086T91P02. The FAA has determined that air safety
and the public interest require the adoption of the rule with this
change, and that this change will neither increase the economic burden
on any operator nor increase the scope of the AD.
There are approximately 1,100 engines of the affected design in the
worldwide fleet. The FAA estimates that 500 engines installed on
aircraft of U.S. registry will be affected by this AD, that it will
take approximately 8 work hours per engine to accomplish the required
actions, and that the average labor rate is $60 per work hour. Parts
will be supplied by the manufacturer to operators under GE's Engine
Care Maintenance Plan (ECMP). At this time, all operators fall under
the ECMP. Based on these figures, the total cost impact of the AD of
U.S. operators is estimated to be $240,000.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
96-26-01 General Electric Aircraft Engines: Amendment 39-9864.
Docket 96-ANE-06.
Applicability: General Electric Aircraft Engines (GE) Models
CT7-5A2, -7A, -9B, and -9C turboprop engines, with gas generator
turbine (GGT) stage 2 forward cooling plates, Part Number (P/N)
6064T10P01 and P/N 5086T91P02, installed. These engines are
installed on but not limited to Construcciones Aeronauticas, SA
(CASA) CN-235 series and SAAB-SCANIA SF340 series aircraft.
Note 1: This airworthiness directive (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 of 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: Required as indicated, unless accomplished
previously.
To prevent GGT stage 2 forward cooling plate failure, which
could result in an uncontained engine failure, accomplish the
following:
(a) Within 30 days after the effective date of this AD, or prior
to reaching the new, reduced cyclic life limits listed in the
Accomplishment Instructions of GE Aircraft Engines (CT7-TP Series)
Service Bulletin (SB) A72-381, dated January 17, 1996, whichever
occurs later, remove from service GGT stage 2 forward cooling
plates, and replace with a serviceable part, which is defined as a
GGT stage 2 forward cooling plate that has less than the new,
reduced cyclic limits on the effective date of this AD, as defined
in that SB.
(b) This action establishes the following new, reduced cyclic
life limits for affected GGT stage 2 forward cooling plates:
(1) 8,000 cycles since new (CSN) for GGT stage 2 forward cooling
plates, P/N 6064T10P01, identified by serial numbers listed in
Tables 1 and 2 of GE Aircraft Engines (CT7-TP Series) SB No. A72-
381, dated January 17, 1996, for GE CT7-5A2, -7A, -9B, and -9C
engine models.
(2) 12,000 CSN for GGT stage 2 forward cooling plates, P/N
6064T10P01 (not listed in (1) above), and P/N 5086T91P02, for GE
CT7-5A2 and -7A engine models.
(3) 9,000 CSN for GGT stage 2 forward cooling plates, P/N
6064T10P01 (not listed in (1) above), and P/N 5086T91P02, for GE
CT7-9B/-9C engine models.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
[[Page 1041]]
used if approved by the Manager, Engine Certification Office. The
request should be forwarded 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.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(e) Thereafter, except as provided in paragraphs (c) and (d) of
this AD, no alternative replacement times may be approved for GGT
stage 2 forward cooling plates, P/N 6064T10P01, and P/N 5086T91P02.
(f) The actions required by this AD shall be done in accordance
with the following GE Aircraft Engines (CT7-TP Series) SB:
------------------------------------------------------------------------
Document No Pages Date
------------------------------------------------------------------------
A72-381............................ 1-13 Jan. 17, 1996.
Total Pages: 13.
------------------------------------------------------------------------
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from GE Aircraft Engines, 1000
Western Ave., Lynn, MA 01910; telephone (617) 594-3140, fax (617)
594-4805. Copies may be inspected at the FAA, New England Region,
Office of the Assistant Chief Counsel, 12 New England Executive
Park, Burlington, MA; or at the Office of the Federal Register, 800
North Capitol Street NW., suite 700, Washington, DC.
(g) This amendment becomes effective on March 10, 1997.
Issued in Burlington, Massachusetts, on December 16, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 97-474 Filed 1-7-97; 8:45am]
BILLING CODE 4910-13-U
