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publication of this proposed rule.
For the reasons discussed above, I
certify that this proposed regulation (1)
is not a ‘‘significant regulatory action’’
under Executive Order 12866; (2) is not
a ‘‘significant rule’’ under the DOT
Regulatory Policies and Procedures (44
FR 11034, February 26, 1979); and (3) if
promulgated, will not have a significant
economic effect, positive or negative, on
a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act. A copy of the draft
regulatory evaluation prepared for this
action is contained in the Rules Docket.
A copy of it may be obtained by
contacting the Rules Docket at the
location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend 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.
§ 39.13 [Amended]
2. Section 39.13 is amended by
removing Amendment 39–11698 (65 FR
21638, April 24, 2000), and by adding
a new airworthiness directive, to read as
follows:
General Electric Company: Docket No. 98–
ANE–49–AD. Supersedes AD 2000–08–
12, Amendment 39–11698.
Applicability: This airworthiness directive
(AD) is applicable to General Electric
Company (GE) CF6–80A, CF6–80C2, and
CF6–80E1 series turbofan engines, installed
on but not limited to Airbus Industrie A300,
A310, and A330 series, Boeing 747 and 767
series, and McDonnell Douglas MD–11 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 done.
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
manufacturer’s Life Limits Section of the
Instructions for Continued Airworthiness
(ICA), 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 instructions provided in
the applicable manual provisions:
Part nomenclature Part No. (P/N) Inspect per engine manual chapter
For CF6–80A Engines:
Disk, Fan Rotor Stage 1 ............................................ All ....................................... 72–21–03 Paragraph 3. Fluorescent-Penetrant Inspect,
and
72–21–03 Paragraph 4. Eddy Current Inspect.
Fan Forward Shaft ..................................................... All ....................................... 72–21–05 Paragraph 2. Magnetic Particle Inspect.
Fan Mid Shaft ............................................................ All ....................................... 72–24–01 Paragraph 2. Magnetic Particle Inspect.
Disk, HPC Rotor, Stage One .................................... All ....................................... 72–31–04 Paragraph 3. Fluorescent-Penetrant Inspect.
Disk, HPC Rotor, Stage Two .................................... All ....................................... 72–31–05 Paragraph 3. Fluorescent-Penetrant Inspect.
Spool, HPC Rotor, Stage3–9 .................................... All ....................................... 72–31–06 Paragraph 3. Fluorescent-Penetrant Inspect.
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