Federal Aviation Administration (FAA), DOT.
Final rule; request for comments.
The FAA is adopting a new airworthiness directive (AD) for Teledyne Continental Motors (TCM) models 520 and 550 series engines with certain ECi cylinders installed. This AD requires replacing certain serial-numbered (SN) cylinders supplied by ECi before further flight. This AD results from reports of 34 failures of cylinder heads marketed by ECi. We are issuing this AD to prevent loss of engine power due to cracks in the cylinder head and possible engine failure caused by separation of a cylinder head.
This AD becomes effective May 5, 2004.
We must receive any comments on this AD by June 21, 2004.
Use one of the following addresses to submit comments on this AD:
- By mail: The Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2004-NE-07-AD, 12 New England Executive Park, Burlington, MA 01803-5299.
- By fax: (781) 238-7055.
- By e-mail: email@example.com.
You can get the service information referenced in this AD from Engine Components, Inc., 9503 Middlex, San Antonio, TX 78217; Phone (210) 820-8100; fax (210) 820-3103.
You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Fred Stellar, Branch Manager, Special Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76193; telephone (817) 222-5199; fax (817) 222-5785.End Further Info End Preamble Start Supplemental Information
On February 1, 2003, we received a report of an ECi cylinder head, part number (P/N) AEC65385, that separated from the barrel at the head-to-barrel junction. Since that report, we have received reports of 27 additional ECi cylinder heads that had the same condition. We also received reports of six cylinder heads that had a crack between the 9th and 10th head fin from the head-to-barrel junction. All of the reported separations and cracks were located between the ninth and tenth head fin from the head-to-barrel junction. All of the cracks started on the exhaust side of the head. The ECi cylinder head, P/N AEC65385, is part of ECi cylinder, P/N AEC631397. RAM Series III, IV, and VII reciprocating engines are the primary users of these cylinders. The RAM series engines are TCM TSIO-520-NB, -VB, and -WB engines that are modified by supplemental type certificate (STC) SE4327SW, STC SE09104SC, or STC SE09261SC for operation at 325 HP or greater. In addition, we approved the engine cylinders, ECi P/N AEC631397 for use on TCM models 520 and 550 series reciprocating engines under a Parts Manufacturer Approval (PMA). The Airmotive Engine Division of ECi holds the PMA. ECi markets the parts as ECi parts.
Results of Manufacturer's Investigation
An investigation by ECi revealed that cylinder heads, P/N AEC65385, manufactured between September 1, 2002, and May 12, 2003, SNs 1044 through 7708, are susceptible to an over-hardened condition, which reduces the fatigue strength of the cylinder. It also increases the chance that the cylinder will crack.
Relevant Service Information
We reviewed and approved the technical contents of RAM Aircraft Mandatory Service Bulletin (MSB) MSB2003-02, dated August 8, 2003, and ECi MSB S.I. No. 04-1, Revision 1, dated March 11, 2004, that describe procedures for identifying, inspecting, and replacing affected cylinders.
Differences Between This AD and the Service Information
RAM Aircraft MSB MSB2003-02, dated August 8, 2003, requires replacing only the No. 6 cylinder, ECi P/N AEC631397, on RAM Series III, IV, and VII engines. ECi MSB S.I. No. 04-1, Revision 1, dated March 11, 2004, requires identifying the suspect cylinders on TCM models 520 and 550 engines and inspecting them for cracks. This AD requires replacing all cylinders, ECi P/N AEC631397, on all RAM Series III, IV, and VII engines; a\nd all TCM model 520, and 550 series engines.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or develop on other RAM Series III, IV, and VII engines; and TCM model 520, and 550 series engines of the same type design. We are issuing this AD to prevent loss of engine power due to cracks in the cylinder head and possible engine failure caused by separation of a cylinder head. This AD requires:
- Performing a check to identify cylinders, ECi P/N AEC631397, S/Ns 1044 through 7708, within 50 hours time-in-service after the effective date of this AD. and
- If a cylinder has an affected P/N and SN, replacing the cylinder before further flight if it was not inspected at ECi.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days.
This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include “AD Docket No. 2004-NE-07-AD” in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket Start Printed Page 21050number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments.
We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications with you. You can get more information about plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.
Examining the AD Docket
You may examine the AD Docket (including any comments and service information), by appointment, between 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location.
We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “AD Docket No. 2004-NE-07-AD” in your request.Start List of Subjects
List of Subjects in 14 CFR Part 39
- Air transportation
- Aviation safety
Adoption of the AmendmentStart Amendment Part
Accordingly, under 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:End Amendment Part Start Part
PART 39—AIRWORTHINESS DIRECTIVESEnd Part Start Amendment Part
1. The authority citation for part 39 continues to read as follows:End Amendment Part
2. The FAA amends § 39.13 by adding the following new airworthiness directive:End Amendment Part
2004-08-10 Engine Components Incorporated (ECi): Amendment 39-13579. Docket No. 2004-NE-07-AD.
(a) This airworthiness directive (AD) becomes effective May 5, 2004.
(c) This AD applies to Teledyne Continental Motors (TCM) TSIO-520-NB, -VB, and -WB engines that are modified by supplemental type certificate (STC) SE4327SW, STC SE09104SC, or STC SE09261SC for operation at 325 HP or greater, (the so-called RAM TSIO-520-NB, -VB, or -WB Series III, IV, and VII reciprocating engines; and Teledyne Continental Motors (TCM) model 520 and 550 series reciprocating engines with certain ECi reciprocating engine cylinders, part number (P/N) AEC631397, installed. These engines are installed on, but not limited to the airplanes listed in the following Table 1:
|Airplane manufacturer and model||Engine model|
|AERFER/AERMECCHI AM, 3||GTSIO-520-C|
|500A COLEMILL CONVERSION||IO-520-E|
|AISA: F20, PEGASO||IO-520-K|
|BEAGLE (U.K.): B206S||GTSIO-520-C|
|BEECHCRAFT DEBONAIR: C33A||IO-520-B|
|VIKING 300||IO-520-A IO-520-D IO-520-K|
|BONNAIRE 188 CONVERSION||IO-520-D|
|SUPER SKYLANE A, B, C, D, E||IO-520-A|
|TURBO SUPER SKYLANE||TSIO-520-C|
|SKYWAGON A185 E,F||IO-520-D|
|AG SPRAYER 188-300||IO-520-D|
|AG TRUCK (A 188B) -300||IO-520-D|
|AG HUSKEY (A 188C) -310||TSIO-520-T|
|AG WAGON (A 188B)||IO-520-D|
|SUPER SKYWAGON U206, A||IO-520-A|
|U206B, C, D, E, F||IO-520-F|
|TURBO SKYWAGON TU206 A||IO-520-C|
|TU206B, C, D, E, F||TSIO-520-C|
|SUPER SKYLANE P206A||IO-520-A|
|P206B, C, D, E||IO-520-A|
|TURBO P 206 A, B, C, D, E||TSIO-520-C|
|STATIONAIR 207A, 207AII||IO-520-F|
|STATIONAIR 8, 811||IO-520-F|
|Start Printed Page 21051|
|210 CENTURION D, E, F, G, H||IO-520-A|
|210 CENTURION J||IO-520-J|
|210 CENTURION K, L, M, N, R||IO-520-L|
|210 CENTURION TURBO||TSIO-520-C|
|210 CENTURION TURBO||TSIO-520-H|
|210 CENTURION TURBO K, L||TSIO-520-H|
|TURBO 210 J, K, L||TSIO-520-H|
|TURBO 210 MII, NII||TSIO-520-R|
|PRESSURIZED CENTURION P210N||TSIO-520-P|
|PRESSURIZED CENTURION P210NII||TSIO-520-AF|
|PRESSURIZED CENTURION P210R||TSIO-520-CE|
|TURBO 310 P, Q||TSIO-520-B|
|TURBO 310 R||TSIO-520-BB|
|TURBO 310 R||TSIO-520-B|
|EXECUTIVE SKYNIGHT D, E, F||TSIO-520-B|
|401 A, 401 B||TSIO-520-E|
|402 A, 402 B||TSIO-520-E|
|414, 414 A||TSIO-520-NB, -N|
|RANGEMASTER MODEL H||IO-520-B|
|RANGEMASTER MODEL H||IO-520-BA|
|DE HAVILLAND HERON||IO-520-E|
(d) This AD results from reports of 34 failures of ECi cylinder head. We are issuing this AD to prevent loss of engine power due to cracks in the cylinder head and possible engine failure caused by separation of a cylinder head.
(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
Identifying Suspect Cylinders
(f) Within 50 hours time-in-service (TIS) after the effective date of this AD, identify, and if necessary replace cylinders, ECi P/N AEC631397 as follows:
(1) Identify the cylinder serial number (SN) as follows:
(i) Determine the SN of the cylinder by looking in the engine records or by inspecting the cylinder for a SN on the intake port boss (see Figure 1) or on the flat area next to the head to barrel junction (see Figure 2). Disregard any dash numbers that might follow the four digit SN.Start Printed Page 21052
(ii) If the SN is 1043 or lower, or if it is 7709 or higher, no further action is required.
(2) If the cylinder SN is 1044 through 7708, do the following:
(i) Remove the rocker box cover from the cylinder.
(ii) Look at the left-front cylinder casting.
(iii) If the casting has AEC65385, and an “O” under the ECi logo, the cylinder is P/N AEC631397. See Figure 3.
(iv) If the cylinder is not ECi P/N AEC631397, no further action is required.
(3) If the cylinder is ECi P/N AEC631397, do the following:
(i) Look at the flange of the rocker box.Start Printed Page 21053
(ii) If there is a letter “A,” “B,” or “X” stamped on the flange of the rocker box, no further action is required. See Figure 4.
(iii) If there is no letter “A,” “B,” or “X” stamped on the flange of the rocker box, replace the cylinder before further flight.
Alternative Methods of Compliance
(g) The Manager, Special Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(i) ECi Mandatory Service Bulletin S.I. No. 04-1, revision 1, dated March 11, 2004, also pertains to this subject of this AD.Start Signature
Issued in Burlington, Massachusetts, on April 9, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 04-8877 Filed 4-19-04; 8:45 am]
BILLING CODE 4910-13-P