AD 2002-12-09

[Federal Register Volume 67, Number 117 (Tuesday, June 18, 2002)]
[Rules and Regulations]
[Pages 41318-41323]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-14855]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-39-AD; Amendment 39-12781; AD 2002-12-09]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. (Formerly 
AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-11U, -12B, 
-12JR, -12UA, -12UAR, and -12UHR Series Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Honeywell International Inc. (formerly AlliedSignal 
Inc. and Garrett Turbine Engine Company) TPE331-11U, -12B, -12JR, -
12UA, -12UAR, and -12UHR series turboprop engines. This action requires 
repetitive Spectrometric Oil Analysis Program (SOAP) sampling, SOAP 
trend assessment, and inspections and replacement of certain gearbox 
components. This amendment is prompted by reports of spur gearshaft 
(bull gear) rim separations and high-speed pinion (HSP) assembly 
failures. The actions specified in this AD are intended to prevent bull 
gear rim separations and HSP assembly failures from abnormal gear wear, 
which could result in uncontained gearbox fragmentation, in-flight 
shutdowns, and engine rotor overspeed events.

DATES: Effective July 3, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of July 3, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before August 19, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-39-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: <a href="/cdn-cgi/l/email-protection#caf3e7aba4afe7abaea9a5a7a7afa4be8aacababe4ada5bc"><span class="__cf_email__" data-cfemail="1d24307c7378307c797e7270707873695d7b7c7c337a726b">[email&#160;protected]</span></a>. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained from 
Honeywell Engines, Systems and Services, Technical Data Distribution, 
M/S 2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone: (602) 
365-2493 (General Aviation), (602) 365-5535 (Commercial); fax: (602) 
365-5577 (General Aviation and Commercial). This information may be 
examined, by appointment, at the FAA, New England Region, Office of the 
Regional 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: Joseph Costa, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone 
(562) 627-5246; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: There have been 22 reported spur gearshaft 
(bull gear) rim separations and 25 HSP assembly failures in Honeywell 
TPE331-11 and -12 series turboprop engines. These failures caused a 
prop gear train disconnection from the power group and most resulted in 
in-flight shutdowns. Three of the six bull gear separations in TPE331-
11U series engines occurred after the bull gears had previously been 
operated in TPE331-12UA, -12UA, or -12UHR series engines. There have 
been 10 incidents of gear fragments penetrating the gearbox housing in 
16 of the bull gear rim separation events in TPE331-12UA, -12UA, or -
12UHR series engines. Similarly, there have been three reported 
incidents of gear fragments penetrating the gearbox housing in six of 
the bull gear rim separation events in TPE331-11U series engines. In 
one case in a TPE331-11U series engine and in two cases in TPE331-12 
series engines, oil was ingested through the inlet after the 
uncontained gear fragmentation that resulted in surge, uncommanded 
engine shutdown, and secondary engine damage. In addition, there have 
been five incidents of gearbox debris or uncontained bull gear 
fragments being ejected from the engine's inlet which were then struck 
by the propeller and redirected against the aircraft fuselage. In one 
of these incidents, a bull gear fragment from a TPE331-12UAR series 
engine penetrated the cabin.
    The FAA has determined that high loading between the bull gear and 
HSP gears, bull gear tooth profile, and distortion of the intermediate 
gearbox housings cause abnormal gear wear and subsequent failures of 
the bull gear and HSP. Even though the gearbox in the TPE331-12 series 
engine is similar to the TPE331-11U series engine, the TPE331-12 series 
engines, which have experienced more failures than TPE331-11U series 
engines, have accumulated more time at higher load than in the TPE331-
11U series engine. In addition, coatings used for vibration dampening,

[[Page 41319]]

and surface finish may influence bull gear tooth wear. This condition, 
if not corrected, could result in separation of the bull gear and 
uncontainment of low energy fragments that can damage the engine or the 
aircraft and may injure passengers. Also, engine surge or uncontained 
rotor overspeed due to oil ingestion through the engine inlet may 
occur. The FAA has determined that abnormal gear wear can be detected 
using Spectrometric Oil Analysis Program (SOAP) sampling and SOAP trend 
assessment.
    The FAA has determined that Honeywell's automated trend assessment 
program is the best method to predict the premature failure of the bull 
gear. Honeywell's trend assessment program dictates a particular format 
for data from each SOAP test sample. That format is used by Honeywell's 
approved SOAP labs and the labs have met all the testing procedures, 
standards, reporting requirements established by the FAA. In addition, 
the Honeywell approved SOAP labs have demonstrated the necessary speed 
and efficiency in determining the sample's acceptance, and in 
transferring data to Honeywell's automated trend assessment program. 
Therefore, the FAA is requiring that operators use Honeywell's approved 
SOAP labs in order to allow the use of Honeywell's trend assessment 
program, thereby increasing the likelihood that a premature failure of 
a bull gear will be identified before failure.
    Due to the continued operation of gears that are misaligned, high-
cycle fatigue damage of the bull gear, HSP, and the torque shaft 
assembly with its nut and pin may occur and may be undetectable. The 
FAA has determined that these components will never be serviceable for 
continued aircraft use. However, bull gears and HSP's that are removed 
as unserviceable during subsequent recurrent inspections after improved 
gearbox alignment may be retained as matched sets for possible future 
aircraft use. After the publication of this AD, the FAA might in the 
future, permit gears removed during recurrent and unscheduled 
inspections to be returned to service after appropriate inspections. 
However, Honeywell has informed the FAA that they will not provide 
acceptance criteria for returning these parts to service.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of the 
following Honeywell International Inc. Alert Service Bulletins (ASB):
    <bullet> TPE331-A79-0034, Revision 3, dated October 2, 2001 or 
Revision 4 dated April 5, 2002 describes procedures for a repetitive 
engine oil and filter SOAP sampling and assessment and lists 
Honeywell's Authorized SOAP Labs.
    <bullet> TPE331-A72-2087 dated October 10, 2001 and Revision 1 
dated November 16, 2001; TPE331-A72-2088 dated October 10, 2001, 
Revision 1 dated November 16, 2001, and Revision 2, dated February 20, 
2002; TPE331-A72-2092 dated October 10, 2001 and Revision 1 dated 
November 16, 2001; and TPE331-A72-2093 dated October 10, 2001 and 
Revision 1 dated November 16, 2001 describe procedures for the 
inspection and replacement of gearbox components.
    <bullet> TPE331-72-2090RWK dated October 10, 2001, TPE331-72-
2091RWK dated October 10, 2001; TPE331-72-2094RWK dated October 10, 
2001; and TPE331-72-2095RWK dated October 10, 2001, describe procedures 
for the rework of gearbox components.

FAA's Determination of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Honeywell International Inc. (formerly 
AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-11U, -12B, 
-12JR, -12UA, -12UAR, and -12UHR series turboprop engines of the same 
type design, this AD is being issued to prevent bull gear rim 
separations and HSP assembly failures from abnormal gear wear, which 
could result in uncontained gearbox fragmentation, in-flight shutdowns, 
and engine rotor overspeed events by requiring:
    <bullet> Repetitive SOAP and filter analyses combined with special 
trend assessments, and
    <bullet> Repetitive inspections of certain gearbox components, 
replacement of specific gears, and if necessary, the rework of gearbox 
components.
    These actions must be done in accordance with the service bulletins 
described previously.

Immediate Adoption of This AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-39-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared

[[Page 41320]]

and placed in the Rules Docket. A copy of it, if filed, 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:

2002-12-09  Honeywell International Inc.: Amendment 39-12781. Docket 
No. 2001-NE-39-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Honeywell International Inc. (formerly AlliedSignal Inc. and 
Garrett Turbine Engine Company) TPE331-11U, -12B, -12JR, -12UA, -
12UAR, and -12UHR series turboprop engines. These engines are 
installed on, but not limited to, Fairchild SA227 series (Metro), 
and Jetstream 3201 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 (i) 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 bull gear rim separations and high-speed pinion (HSP) 
assembly failures from abnormal gear wear, which could result in 
uncontained gearbox fragmentation, in-flight shutdowns, engine rotor 
overspeed events, do the following:
    (a) Except for the TPE331-12JR engine series, submit 
Spectrometric Oil Analysis Program (SOAP) samples of the oil and 
filter to Honeywell approved labs in accordance with Paragraph 2. A. 
(1) of the Accomplishment Instructions of Honeywell International 
Inc. Alert Service Bulletin (ASB) TPE331-A79-0034 Revision 3 dated 
October 3, 2001 or Revision 4 dated April 5, 2002, at 80 to 120 
hours time-in-service (TIS) after the effective date of this AD and 
at 80 to 120 hour TIS intervals thereafter.
    (b) If either of the following conditions occur, make the 
necessary repairs in accordance with Paragraph 2.A.(3)(b)1 or 
2.A.(3) of the Accomplishment Instructions of Honeywell 
International Inc. ASB TPE331-A79-0034 Revision 3, dated October 3, 
2001; or Revision 4, dated April 5, 2002, within 50 hours TIS after 
receiving the results from the unacceptable sample analysis or trend 
assessment:
    (1) If the SOAP test lab sample is determined to be unacceptable 
in accordance with Paragraph 2.A.(2)(b)1 in the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A79-0034 
Revision 3 dated October 3, 2001 or Revision 4 dated April 5, 2002, 
or
    (2) If Honeywell's supplementary trend assessment is 
unacceptable in accordance with Paragraph 2.A.(3) in the 
Accomplishment Instructions of Honeywell International Inc. ASB 
TPE331-A79-0034 Revision 3 dated October 3, 2001; or Revision 4 
dated April 5, 2002.

TPE331-12UA, -12UAR, and -12UHR Engine Maintenance

    (c) On TPE331-12UA, -12UAR, and -12UHR engines, inspect, 
replace, and if necessary, rework specified gearbox components as 
follows:
    (1) At the next turbine (hot) section inspection, gearbox 
inspection, engine overhaul, or when the gearbox diaphragm module is 
out of the engine, whichever occurs first, after the effective date 
of this AD, comply with the following:
    (i) Paragraphs 2.A. (2) through 2.A. (11) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2087, 
Revision 1, dated November 16, 2001 or ASB TPE331-A72-2087, dated 
October 10, 2001.
    (ii) Paragraphs 2.A. (2) through 2.A. (8) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2090RWK, 
dated October 10, 2001.
    (iii) Paragraphs 2.A. (2) through 2.D. (4) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2091RWK, 
dated October 10, 2001.
    (2) Thereafter, do the following:
    (i) Inspect for wear and replace gearbox components and comply 
with limitations on interchangeability in accordance with Paragraphs 
2.B. and 2.C. (2) through 2.C. (13) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2087, 
Revision 1, dated November 16, 2001 or ASB TPE331-A72-2087, dated 
October 10, 2001 at intervals not to exceed 3,600 hours TIS since 
the last replacement of the bull gear, part number (P/N) 3108295-1, 
and the HSP, P/N 3101741-2, or since the last overhaul of the 
diaphragm matched housing set, whichever occurs first.
    (ii) Comply with limitations on interchangeability in accordance 
with Paragraph 2.B. of the Accomplishment Instructions of Honeywell 
International Inc. ASB TPE331-A72-2087, Revision 1, dated November 
16, 2001 or ASB TPE331-A72-2087, dated October 10, 2001 whenever 
certain gearbox parts, identified in Paragraph 2.B. of ASB TPE331-
A72-2087, are removed from the engine following compliance with 
paragraph (c)(1) or (c)(2)(i) of this AD.
    (iii) Comply with limitations on interchangeability and inspect 
for wear in accordance with Paragraphs 2.B. and 2.D. of the 
Accomplishment Instructions of Honeywell International Inc. ASB 
TPE331-A72-2087, Revision 1, dated November 16, 2001 or ASB TPE331-
A72-2087, dated October 10, 2001 whenever the engine is removed from 
the aircraft and disassembled to the extent that the diaphragm 
module is accessed after 500 hours TIS following compliance with 
paragraph (c)(1) or (c)(2)(i) of this AD.

TPE331-12B Engines

    (d) On TPE331-12B engines, inspect, replace, and if necessary, 
rework specified gearbox components as follows:
    (1) At the next engine overhaul or when the bull gear first 
requires replacement, whichever occurs first, after the effective 
date of this AD, comply with the following:
    (i) Paragraphs 2.A. (2) through 2.A. (11) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2092, 
Revision 1, dated November 16, 2001 or ASB TPE331-A72-2092, dated 
October 10, 2001.
    (ii) Paragraphs 2.A. (2) through 2.A. (8) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2094RWK, 
dated October 10, 2001.
    (iii) Paragraphs 2.A. (2) through 2.C. (4) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2095RWK, 
dated October 10, 2001.
    (2) Thereafter, do the following:
    (i) Inspect for wear and replace gearbox components and comply 
with limitations on interchangeability in accordance with Paragraphs 
2.B. and 2.C. (2) through 2.C. (13) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2092, 
Revision 1, dated November 16, 2001 or ASB TPE331-A72-2092, dated 
October 10, 2001, at intervals not to exceed 3,100 hours TIS since 
the last replacement of the bull gear, P/N 3108296-1, and the HSP, 
P/N 3101741-4, or since the last overhaul of the diaphragm matched 
housing set, whichever occurs first.
    (ii) Comply with limitations on interchangeability in accordance 
with Paragraph 2.B. of the Accomplishment Instructions of Honeywell 
International Inc. ASB TPE331-A72-2092, Revision 1, dated November 
16, 2001 or ASB TPE331-A72-2092, dated October 10, 2001, whenever 
certain gearbox parts, identified in Paragraph 2.B. of ASB TPE331-
A72-2092, are removed from the engine following compliance with 
paragraph (d)(1) or (d)(2)(i) of this AD.
    (iii) Comply with limitations on interchangeability and inspect 
for wear in accordance with Paragraphs 2.B. and 2.D. of the 
Accomplishment Instructions of Honeywell International Inc. ASB 
TPE331-A72-2092, Revision 1, dated November 16, 2001 or ASB TPE331-
A72-2092, dated

[[Page 41321]]

October 10, 2001, whenever the engine is removed from the aircraft 
and disassembled to the extent that the diaphragm module is accessed 
after 500 hours TIS following compliance with paragraphs (d)(1) or 
(d)(2)(i) of this AD.

TPE331-11U Engines With Bull Gear P/N 3107161-1

    (e) On TPE331-11U engines with bull gear P/N 3107161-1, inspect, 
replace and if necessary, rework specified gearbox components as 
follows:
    (1) At the next hot section inspection, gearbox inspection, 
engine overhaul, or when the gearbox diaphragm module is out of the 
engine, whichever occurs first after the effective date of this AD, 
comply with the following:
    (i) Paragraphs 2.A. (2) through 2.A. (11) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2088, 
Revision 2, dated February 20, 2002, Revision 1, dated November 16, 
2001, or original, dated October 10, 2001.
    (ii) Paragraphs 2.A. (2) through 2.A. (8) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2090RWK, 
dated October 10, 2001.
    (iii) Paragraphs 2.A. (2) through 2.D. (4) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2091RWK, 
dated October 10, 2001.
    (2) Thereafter, do the following:
    (i) Inspect for wear and replace gearbox components and comply 
with limitations on interchangeability in accordance with Paragraphs 
2.B. and C. (2) through C. (13) of the Accomplishment Instructions 
of Honeywell International Inc. ASB TPE331-A72-2088, Revision 2, 
dated February 20, 2002, Revision 1, dated November 16, 2001 or 
original, dated October 10, 2001, at intervals not to exceed 9,000 
hours time-in-service (TIS) since the last replacement of the bull 
gear, P/N 3108295-1, and the HSP, P/N 3101741-2, or since the last 
overhaul of the diaphragm matched housing set, whichever occurs 
first.
    (ii) Comply with limitations on interchangeability in accordance 
with Paragraph 2.B. of the Accomplishment Instructions of Honeywell 
International Inc. ASB TPE331-A72-2088, Revision 2, dated February 
20, 2002, Revision 1, dated November 16, 2001, or original, dated 
October 10, 2001, whenever certain gearbox parts, identified in 
Paragraph 2.B. of ASB TPE331-A72-2088, are removed from the engine 
following compliance with Paragraph (e)(1) or (e)(2)(i) of this AD.
    (iii) Comply with limitations on interchangeability and inspect 
for wear in accordance with Paragraphs 2.B. and 2.D. of the 
Accomplishment Instructions of Honeywell International Inc. ASB 
TPE331-A72-2088, Revision 2, dated February 20, 2002, Revision 1, 
dated November 16, 2001, or original, dated October 10, 2001 
whenever the engine is removed from the aircraft and disassembled to 
the extent that the diaphragm module is accessed after 500 hours TIS 
following compliance with paragraph (e)(1) or (e)(2)(i) of this AD.

All OtherTPE331-11U Engines Without Bull Gear P/N 3107161-1

    (f) On TPE331-11U engines, that do not have a bull gear, P/N 
3107161-1, inspect, replace, and if necessary, rework specified 
gearbox components as follows:
    (1) At the next gearbox inspection, engine overhaul, or when the 
gearbox diaphragm module is out of the engine, whichever occurs 
first after the effective date of this AD, comply with the 
following:
    (i) Paragraphs 2.A. (2) through 2.A. (11) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2088, 
Revision 2, dated February 20, 2002, Revision 1, dated November 16, 
2001, or original, dated October 10, 2001.
    (ii) Paragraphs 2.A. (2) through 2.A. (8) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2090RWK, 
dated October 10, 2001.
    (iii) Paragraphs 2.A. (2) through 2.D. (4) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2091RWK, 
dated October 10, 2001.
    (2) Thereafter, do the following:
    (i) Inspect for wear and replace gearbox components and comply 
with limitations on interchangeability in accordance with Paragraphs 
2.B. and 2.C. (2) through 2.C. (13) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2088, 
Revision 2, dated February 20, 2002, Revision 1, dated November 16, 
2001, or original, dated October 10, 2001, at intervals not to 
exceed 9,000 hours TIS since the last replacement of the bull gear, 
P/N 3108295-1, and the HSP, P/N 3101741-2, or since the last 
overhaul of the diaphragm matched housing set, whichever occurs 
first.
    (ii) Comply with limitations on interchangeability in accordance 
with Paragraph 2.B. of the Accomplishment Instructions of Honeywell 
International Inc. ASB TPE331-A72-2088, Revision 2, dated February 
20, 2002, Revision 1, dated November 16, 2001, or original, dated 
October 10, 2001, whenever certain gearbox parts, identified in 
Paragraph 2.B.of ASB TPE331-A72-2088, are removed from the engine 
following compliance with Paragraph (f)(1) or (f)(2)(i) of this AD.
    (iii) Comply with limitations on interchangeability and inspect 
for wear in accordance with Paragraphs 2.B. and 2.D.of the 
Accomplishment Instructions of Honeywell International Inc. ASB 
TPE331-A72-2088, Revision 2, dated February 20, 2002, Revision 1, 
dated November 16, 2001, or original, dated October 10, 2001, 
whenever the engine is removed from the aircraft and disassembled to 
the extent that the diaphragm module is accessed after 500 hours TIS 
following compliance with paragraph (f)(1) or (f)(2)(i) of this AD.

TPE331-12JR Engines

    (g) On TPE331-12JR engines, inspect, replace, and if necessary, 
rework specified gearbox components as follows:
    (1) At the next gearbox inspection, engine overhaul, or when the 
bull gear requires replacement, whichever occurs first, comply with 
the following:
    (i) Paragraphs 2.A. (2) through 2.A. (11) of the Accomplishment 
Instructions of Honeywell International Inc. ASB TPE331-A72-2093, 
Revision 1, dated November 16, 2001 or ASB TPE331-A72-2093, dated 
October 10, 2001.
    (ii) Paragraphs 2.A. (2) through 2.A. (8) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2090RWK, 
dated October 10, 2001.
    (iii) Paragraphs 2.A. (2) through 2.D. (4) of the Accomplishment 
Instructions of Honeywell International Inc. SB TPE331-72-2091RWK, 
dated October 10, 2001.
    (2) Thereafter, do the following:
    (i) Inspect for wear and replace gearbox components and comply 
with limitations on interchangeability in accordance with Paragraphs 
2.B. and 2.C. (2) through C. (13) of the Accomplishment Instructions 
of Honeywell International Inc. ASB TPE331-A72-2093, Revision 1, 
dated November 16, 2001 or ASB TPE331-A72-2093, dated October 10, 
2001, at intervals not to exceed 5,100 hours TIS since the last 
replacement of the bull gear, P/N 3108295-1, and the HSP, P/N 
3101741-2, or since the last overhaul of the diaphragm matched 
housing set, whichever occurs first.
    (ii) Comply with limitations on interchangeability in accordance 
with Paragraph 2.B. of the Accomplishment Instructions of Honeywell 
International Inc. ASB TPE331-A72-2093, Revision 1, dated November 
16, 2001 or ASB TPE331-A72-2093, dated October 10, 2001, whenever 
certain gearbox parts, identified in Paragraph 2.B. of ASB TPE331-
A72-2093, are removed from the engine following compliance with 
Paragraph (g)(1) or (g)(2)(i) of this AD.
    (iii) Comply with limitations on interchangeability and inspect 
for wear in accordance with Paragraphs 2.B. and 2.D. of the 
Accomplishment Instructions of Honeywell International Inc. ASB 
TPE331-A72-2093, Revision 1, dated November 16, 2001 or ASB TPE331-
A72-2093, dated October 10, 2001, whenever the engine is removed 
from the aircraft and disassembled to the extent that the diaphragm 
module is accessed after 500 hours TIS following compliance with 
paragraph (g)(1) or (g)(2)(i) of this AD.

Definitions

    (h) For the purposes of this AD, as stated in the incorporated 
service bulletins, the word ``scrap'' must be interpreted as ``not 
serviceable.'' Any reference in these bulletins to the intentional 
damage of gear teeth is not mandatory.

Alternative Methods of Compliance

    (i) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (LAACO). Operators must submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, LAACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the LAACO.


[[Page 41322]]



Special Flight Permits

    (j) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (k) The actions required by this AD must be done in accordance 
with the following Honeywell International Inc. Service Bulletins 
(SB's):

--------------------------------------------------------------------------------------------------------------------------------------------------------
             Document No.                              Pages                                Revision                                Date
--------------------------------------------------------------------------------------------------------------------------------------------------------
ASB TPE331-A79-0034..................  1....................................  4...................................  April 5, 2002.
                                       2....................................  2...................................  July 23, 2001.
                                       3-5..................................  3...................................  October 2, 2001.
                                       6-7..................................  4...................................  April 5, 2002.
                                       8-10.................................  3...................................  October 2, 2001.
Total pages: 10
ASB TPE331-A79-0034..................  1....................................  3...................................  October 2, 2001.
                                       2....................................  2...................................  July 23, 2001.
                                       3-10.................................  3...................................  October 2, 2001.
Total pages: 10
ASB TPE331-A72-2087..................  1....................................  1...................................  November 16, 2001.
                                       2-3..................................  Original............................  October 10, 2001.
                                       4-6..................................  1...................................  November 16, 2001.
                                       7-9..................................  Original............................  October 10, 2001.
                                       10...................................  1...................................  November 16, 2001.
                                       11-13................................  Original............................  October 10, 2001.
                                       14-15................................  1...................................  November 16, 2001.
                                       16...................................  Original............................  October 10, 2001.
                                       17...................................  1...................................  November 16, 2001.
                                       18...................................  Original............................  October 10, 2001.
Total pages: 18
ASB TPE331-A72-2087..................  All..................................  Original............................  October 10, 2001.
Total pages: 18
ASB TPE331-A72-2088..................  1....................................  2...................................  February 20, 2002.
                                       2....................................  Original............................  October 10, 2001.
                                       3-5..................................  1...................................  November 16, 2001.
                                       6-7..................................  Original............................  October 10, 2001.
                                       8....................................  2...................................  February 20, 2002.
                                       9-11.................................  Original............................  October 10, 2001.
                                       12...................................  1...................................  November 16, 2001.
                                       13...................................  2...................................  February 20, 2002.
                                       14...................................  Original............................  October 10, 2001.
                                       15...................................  1...................................  November 16, 2001.
                                       16...................................  Original............................  October 10, 2001.
Total pages: 16
ASB TPE331-A72-2088..................  1....................................  1...................................  November 16, 2001.
                                       2....................................  Original............................  October 10, 2001.
                                       3-5..................................  1...................................  November 16, 2001.
                                       6-7..................................  Original............................  October 10, 2001.
                                       8....................................  1...................................  November 16, 2001.
                                       9-11.................................  Original............................  October 10, 2001.
                                       12-13................................  1...................................  November 16, 2001.
                                       14...................................  Original............................  October 10, 2001.
                                       15...................................  1...................................  November 16, 2001.
                                       16...................................  Original............................  October 10, 2001.
Total pages: 16
ASB TPE331-A72-2088..................  All..................................  Original............................  October 10, 2001.
Total pages: 16
SB TPE331-72-2090RWK.................  All..................................  Original............................  October 10, 2001.
Total pages: 10
SB TPE331-72-2091RWK.................  All..................................  Original............................  October 10, 2001.
Total pages: 12
ASB TPE331-A72-2092..................  1....................................  1...................................  November 16, 2001.
                                       2....................................  Original............................  October 10, 2001.
                                       3-5..................................  1...................................  November 16, 2001.
                                       6-7..................................  Original............................  October 10, 2001.
                                       8....................................  1...................................  November 16, 2001.
                                       9-11.................................  Original............................  October 10, 2001.
                                       12...................................  1...................................  November 16, 2001.
                                       13...................................  Original............................  October 10, 2001.
                                       14...................................  1...................................  November 16, 2001.
                                       15...................................  Original............................  October 10, 2001.
                                       16...................................  1...................................  November 16, 2001.
                                       17-18................................  Original............................  October 10, 2001.
Total pages: 18
ASB TPE331-A72-2092..................  All..................................  Original............................  October 10, 2001.
Total pages: 18

[[Page 41323]]

 
ASB TPE331-A72-2093..................  1....................................  1...................................  November 16, 2001.
                                       2....................................  Original............................  October 10, 2001.
                                       3-4..................................  1...................................  November 16, 2001.
                                       5-7..................................  Original............................  October 10, 2001.
                                       8....................................  1...................................  November 16, 2001.
                                       9-11.................................  Original............................  October 10, 2001.
                                       12-13................................  1...................................  November 16, 2001.
                                       14...................................  Original............................  October 10, 2001.
                                       15...................................  1...................................  November 16, 2001.
                                       16...................................  Original............................  October 10, 2001.
Total pages: 16
ASB TPE331-A72-2093..................  All..................................  Original............................  October 10, 2001.
Total pages: 16
SB TPE331-72-2094RWK.................  All..................................  Original............................  October 10, 2001.
Total pages: 8
SB TPE331-72-2095RWK.................  All..................................  Original............................  October 10, 2001.
Total pages: 8
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 Honeywell Engines, Systems and 
Services, Technical Data Distribution, M/S 2101-201, P.O. Box 29003, 
Phoenix, AZ 85038-9003; telephone: (602) 365-2493 (General 
Aviation), (602) 365-5535 (Commercial); fax: (602) 365-5577 (General 
Aviation and Commercial). Copies may be inspected, by appointment, 
at the FAA, New England Region, Office of the Regional 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.

Effective Date

    (l) This amendment becomes effective on July 3, 2002.

    Issued in Burlington, Massachusetts, on June 5, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-14855 Filed 6-17-02; 8:45 am]
BILLING CODE 4910-13-P