[Federal Register Volume 61, Number 193 (Thursday, October 3, 1996)]
[Proposed Rules]
[Pages 51618-51619]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-25170]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 61, No. 193 / Thursday, October 3, 1996 / 
Proposed Rules  

[[Page 51618]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-ANE-13]
RIN 2120-AA64


Airworthiness Directives; AlliedSignal Inc. TPE331 Series 
Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to AlliedSignal Inc. TPE331 series 
turboprop engines equipped with Woodward fuel controls. This proposal 
would require revising the applicable Emergency Procedures or Abnormal 
Procedures Section of the applicable 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 proposal 
would require replacing or reworking orifice fittings and restrictors, 
which would constitute terminating action to the requirement to revise 
the applicable AFM. This proposal 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 the proposed AD are 
intended to prevent a non-responsive power lever and lack of control of 
engine power.

DATES: Comments must be received by December 2, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 96-ANE-13, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be 
submitted to the Rules Docket by using the following Internet address: 
``[email protected]''. All comments must contain the 
Docket No. 96-ANE-13 in the subject line of the comment. Comments may 
be inspected at this location between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays.
    The service information referenced in the proposed rule 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 
FAA, New England Region, Office of the Assistant Chief Counsel, 12 New 
England Executive Park, Burlington, MA.

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 
(310) 627-5246; fax (310) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 96-ANE-13.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket No. 96-ANE-13, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    The Federal Aviation Administration (FAA) has received reports of 
``no response to power lever movement'' after extended high altitude 
operation (20,000 feet or higher) with outside air temperature (OAT) 
below freezing, in clear air (no visible moisture), and engine anti-
icing ``OFF''. An investigation has revealed that these incidents 
resulted from the inlet temperature and pressure (Pt2) sensor becoming 
blocked by ice caused by very small amounts of moisture accumulated in 
the sensor. Ice blockage of this sensor can produce an erroneous (high) 
pressure signal to the fuel control and thus create a fixed fuel flow 
irrespective of the position of the power lever. Occasional icing of 
the Pt2 sensor is currently not addressed the applicable FAA-approved 
Aircraft Flight Manual (AFM) or Pilot's Operating Handbook (POH). Icing 
of the Pt2 sensor may affect one or both engines simultaneously. This 
condition, if not corrected, could result in a non-responsive power 
lever and lack of control of engine power.
    The FAA has reviewed and approved the technical contents of 
AlliedSignal Inc. Operating Information Letter No. 331-13, dated April 
27, 1995, that recommends actions intended to supplement the applicable 
FAA-approved AFM or POH; Service Bulletin (SB) No. TPE331-73-0236, 
dated July 28, 1995, that describes procedures for replacing the inlet 
temperature and pressure sensor orifice fittings; and SB No. TPE331-73-
0235, dated July 28, 1995, that describes procedures for replacing the 
inlet temperature and pressure sensor orifice fittings and reworking 
the inlet sensor Ps3 restrictors.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require revising the Abnormal

[[Page 51619]]

Procedures or Emergency Procedures Section of the applicable FAA-
approved AFM or POH to include a paragraph relating to a non-responsive 
power lever. In addition, this proposal would require replacing orifice 
fittings and reworking restrictors, which would constitute terminating 
action to the requirement to revise the applicable AFM or POH. The 
actions would be required to be accomplished in accordance with the 
service documents described previously.
    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 would be affected by this proposed AD. The 
FAA estimates that 2,760 engines would need modification in accordance 
with SB No. TPE331-73-0236, dated July 28, 1995, that it would 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 would cost approximately $80 per engine.
    In addition, the FAA estimates that 1,240 engines would need 
modification in accordance with SB No. TPE331-73-0235, dated July 28, 
1995, that it would 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 would cost approximately $80 per engine. 
Based on these figures, the total cost impact of the proposed AD on 
U.S. operators is estimated to be $874,400.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 impact, 
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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

AlliedSignal Inc.: Docket No. 96-ANE-13.

    Applicability: AlliedSignal Inc. 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: 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 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) Within 120 days after the effective date of this AD, or at 
next removal of the Pt2 sensor, whichever occurs first, replace or 
rework orifice fittings and 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 reworking the inlet sensor Ps3 restrictor 
constitutes terminating action to the AFM or POH revision 
requirement stated in paragraph (a) of this AD.
    (c) Within 120 days after the effective date of this AD, or at 
next removal of the Pt2 sensor, whichever occurs first, replace the 
orifice fittings in accordance with the Accomplishment Instructions 
of AlliedSignal Aerospace SB No. TPE331-73-0236, dated July 28, 
1995. Replacing 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. The request should be forwarded through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Los Angeles Aircraft Certification Office.

    Note: 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 
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.

    Issued in Burlington, Massachusetts, on September 19, 1996.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 96-25170 Filed 10-2-96; 8:45 am]
BILLING CODE 4910-13-U