[Federal Register Volume 62, Number 141 (Wednesday, July 23, 1997)]
[Rules and Regulations]
[Pages 39425-39427]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-19267]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-ANE-13; Amendment 39-10084; AD 97-15-10]
RIN 2120-AA64
Airworthiness Directives; AlliedSignal Inc. TPE331 Series
Turboprop Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to AlliedSignal Inc. (formerly Garrett Engine Division and
Garrett Turbine Engine Company) TPE331 series turboprop engines
equipped with Woodward fuel controls, that requires revising the
applicable Emergency Procedures or Abnormal Procedures Section of the
applicable Federal Aviation Administration (FAA)-approved Airplane
Flight Manual (AFM) or Pilot's Operating Handbook (POH) to include a
paragraph relating to a non-responsive power lever. In addition, this
AD requires replacing or reworking orifice fittings and restrictors,
which would constitute terminating action to the requirement to revise
the applicable AFM. This amendment is prompted by reports of occasional
icing of the inlet Pt2 sensor, which can produce an erroneous (high)
pressure signal to the fuel control, causing little or no response to
power lever movement. The actions specified by this AD are intended to
prevent a non-responsive power lever and lack of control of engine
power.
DATES: Effective September 22, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 22, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from AlliedSignal Aerospace, Attn: Data Distribution, M/S 64-
3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone (602)
365-2493, fax (602) 365-5577. 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: 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: 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 AlliedSignal Inc. TPE331 series
turboprop engines equipped with Woodward fuel controls was published in
the Federal Register on October 3, 1996 (61 FR 51618). That action
proposed to require revising the Abnormal Procedures or Emergency
Procedures Section of the applicable Federal Aviation Administration
(FAA)-approved Airplane Flight Manual (AFM) or Pilot's Operating
Handbook (POH) to include a paragraph relating to a non-responsive
power lever. In addition, the notice proposed requiring replacing
orifice fittings and reworking restrictors, which would constitute
terminating action to the requirement to revise the applicable AFM or
POH.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter states that the Ayres S2R series aircraft should be
removed from the AD applicability. The commenter states that the Ayres
aircraft models are certified for Visual Flight Rules (VFR) operations
at 12,000 feet or below, and are not normally operated in the altitude
and temperature environment described in the AD. In addition, the
engine has no anti-ice capability installed in this airplane. Also, the
commenter is not aware of any reports of ``no response to power lever
movement'' regarding this airplane. The FAA does not concur. First, the
AD will apply to all TPE331-3, -5, -6, -10, -11, and -12 engines
equipped with Woodward fuel controls, regardless of what aircraft those
engines are installed on. The list of aircraft is provided for
informational purposes only and is not an exclusive listing of aircraft
on which operators might find the affected engines. In addition, the
FAA is aware that some aircraft may be configured without anti-ice
capability, and, therefore, no action would be required under paragraph
(a), which addresses engines installed on aircraft with engine inlet
ice protection. However, the FAA considers engines without engine anti-
ice capability within the scope of the unsafe condition described in
this AD and therefore, must be modified in accordance with paragraph
(b) or (c) of the AD.
Also, the FAA has considered that no reports were submitted
regarding ``no response to power lever movement'' for the Ayres series
aircraft and that the maximum operating altitude for these aircraft is
12,000 feet. Even though ice blockage of the PT2 sensor and pressure
signal increase is an infrequent phenomena and may be influenced by
engine installation, flight operation, and environmental factors, the
FAA has decided to implement the engine orifice fitting and restrictor
modifications based on engine design similarity and the possibility
that the sensor can ice up at lower altitudes in clear air given the
right combination of temperature, relative humidity and airspeed.
Therefore, the Ayres series aircraft will remain in the AD
applicability.
[[Page 39426]]
The FAA has determined that the paragraphs (b) and (c) of the
compliance section might be read ambiguously and that both paragraphs
would have to be complied with when the intent is that engines affected
by AlliedSignal Aerospace Service Bulletin (SB) No. TPE331-73-0235,
dated July 28, 1995, must comply with paragraph (b) and engines
affected by AlliedSignal Aerospace SB No. TPE331-73-0236, dated July
28, 1995, must comply with paragraph (c). The FAA has revised the
compliance section of this final rule accordingly to clear up the
possible ambiguity.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
There are approximately 9,438 engines of the affected design in the
worldwide fleet. The FAA estimates that 4,700 engines installed on
aircraft of U.S. registry will be affected by this AD. The FAA
estimates that 2,760 engines will need modification in accordance with
AlliedSignal Aerospace SB No. TPE331-73-0236, dated July 28, 1995, that
it will take approximately 2 work hours per engine to accomplish the
proposed actions, and that the average labor rate is $60 per work hour.
Required parts will cost approximately $80 per engine.
In addition, the FAA estimates that 1,240 engines will need
modification in accordance with AlliedSignal Aerospace SB No. TPE331-
73-0235, dated July 28, 1995, that it will take approximately 3 work
hours per engine to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts will cost
approximately $80 per engine. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $874,400.
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:
97-15-10 AlliedSignal Inc.: Amendment 39-10084. Docket 96-ANE-13.
Applicability: AlliedSignal Inc. (formerly Garrett Engine
Division and Garrett Turbine Engine Company) TPE331-3, -5, -6, -10,
-11, -12 series turboprop engines equipped with Woodward fuel
controls, installed on but not limited to the following aircraft:
Ayres S2R-G5, S2R-G6, and S2R-G10; Beech Model B100; Construcciones
Aeronauticas, S.A. (CASA) C-212 series; Dornier 228 series;
Fairchild SA226 and SA227 series; Jetstream 3101 and 3201 series;
Mitsubishi MU-2B series (MU-2 series); Short Brothers plc Model SC-7
Skyvan Series 3; Twin Commander Aircraft Corp. 680, 690 and 695
series.
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 (d) 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: Required as indicated, unless accomplished
previously.
To prevent a non-responsive power lever and lack of control of
engine power, accomplish the following:
(a) Within 30 days after the effective date of this AD, for
aircraft equipped with engine inlet ice protection, revise the
applicable Emergency Procedures or Abnormal Procedures Section of
the applicable Federal Aviation Administration (FAA)-approved
Airplane Flight Manual (AFM) or Pilot's Operating Handbook (POH) to
include the following paragraph relating to a non-responsive power
lever. This may be accomplished by inserting a copy of this AD in
the AFM or POH:
``NON-RESPONSIVE POWER LEVER: If a lack of response to the power
lever is observed, turn ON the ignition and engine anti-ice for both
engines. After the condition has cleared and normal operation is
observed, which occurs in approximately three minutes, anti-ice and
ignition can be turned OFF.''
(b) For engine models TPE331-3U-303G, -3UW-303G, -3U-304G, and
engine series TPE331-10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U,
-12UA, -12UAR, and -12UHR, within 120 days after the effective date
of this AD, or at next removal of the Pt2 sensor, whichever occurs
first, replace orifice fittings and replace or rework restrictors in
accordance with the Accomplishment Instructions of AlliedSignal
Aerospace Service Bulletin (SB) No. TPE331-73-0235, dated July 28,
1995. Replacing the orifice fittings and replacing or reworking the
inlet sensor Ps3 restrictor, constitutes terminating action to the
AFM or POH revision requirement stated in paragraph (a) of this AD.
(c) For engine model TPE331-3U-303V and engine series TPE331-5,
-5A, -5AB, -5B, -6, -6A, -10, -10GP, -10GT, -10P, -10R, and -10T,
within 120 days after the effective date of this AD, or at next
removal of the Pt2 sensor, whichever occurs first, replace orifice
fittings in accordance with the Accomplishment Instructions of
AlliedSignal Aerospace SB No. TPE331-73-0236, dated July 28, 1995.
Replacing the orifice fittings constitutes terminating action to the
AFM or POH revision requirement stated in paragraph (a) of this AD.
(d) 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. Operators shall submit their requests through an appropriate
FAA Principal Maintenance Inspector, who may add comments and then
send it to the Manager, Los Angeles Aircraft 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 Los Angeles Aircraft Certification
Office.
(e) Special flight permits may be issued in accordance with
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR
21.197
[[Page 39427]]
and 21.199) to operate the aircraft to a location where the
requirements of this AD can be accomplished.
(f) The actions required by this AD shall be done in accordance
with the following AlliedSignal Aerospace SBs:
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Document No. Pages Date
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TPE331-73-0235................... 1-10 July 28, 1995.
Total........................ 10
TPE331-73-0236................... 1-8 July 28, 1995.
Total........................ 8
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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 AlliedSignal Aerospace, Attn:
Data Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix, AZ
85038-9003; telephone (602) 365-2493, fax (602) 365-5577. 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 September 22, 1997.
Issued in Burlington, Massachusetts, on July 10, 1997.
Ronald L. Vavruska,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 97-19267 Filed 7-22-97; 8:45 am]
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