AD 97-15-10

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.

Final rule.

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 POHrevision 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 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.

(f) The actions required by this AD shall be done in accordance with the following AlliedSignal Aerospace SBs:

Document No
Pages
Date
TPE331-73-0235
1-10
July 28, 1995 Total Pages: 10.
TPE331-73-0236
1-8
July 28, 1995
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 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.

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.

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 increasethe 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.

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