Airworthiness Directives; Bombardier-Rotax GmbH Type 912 F, 912 S, and 914 F Series Reciprocating Engines

[Federal Register Volume 67, Number 159 (Friday, August 16, 2002)]
[Rules and Regulations]
[Pages 53473-53475]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20266]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-17-AD; Amendment 39-12846; AD 2002-16-07]
RIN 2120-AA64


Airworthiness Directives; Bombardier-Rotax GmbH Type 912 F, 912 
S, and 914 F Series Reciprocating Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain serial numbers (SN's) of Bombardier-Rotax GmbH 
type 912 F, 912 S and 914 F series reciprocating engines. This action 
requires replacement of the valve spring retainers, part number (P/N) 
854.182, with the new-reinforced valve spring retainers, P/N 854.184. 
This amendment is prompted by reports of several cracked valve spring 
retainers discovered in-service. The actions

[[Page 53474]]

specified in this AD are intended to prevent cracking of the valve 
spring retainers resulting in possible engine failure while in-flight.

DATES: Effective September 3, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of September 3, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before October 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-17-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 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: ``[email protected]''. 
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 
Bombardier-Rotax GmbH, Welser Strasse 32, A-4623 Gunskirchen, Austria; 
telephone 7246-601-232; fax 7246-601-370. Information regarding this 
action 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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park; Burlington, MA 01803-5299; telephone 781 
238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: Austro Control, which is the airworthiness 
authority for Austria, notified the FAA that an unsafe condition may 
exist on certain SN's of Bombardier-Rotax GmbH type 912 F, 912 S, and 
914 F series reciprocating engines, that have been converted to a 
single valve spring arrangement. Austro Control advises that they have 
received reports of several cracks on valve spring retainers in-
service. It has been discovered that during the starting procedure a 
delayed purging of the lubrication system could occur, which may result 
in cracking of the valve spring retainer. This condition can occur if 
one or more hydraulic valve tappets lose their oil prime and fill with 
air. This is possible at first engine run or at oil change. This 
condition can be caused by improper purging of the lubrication system, 
non-compliance of starting and warming up instructions, unsuitable 
motor oil, or lack of maintenance. A detailed crack detection of the 
affected valve spring retainers is very difficult and would have to be 
performed repeatedly. Due to this fact, all affected engines must be 
equipped with reinforced valve spring retainers that are more resistant 
to cracking.

Manufacturer's Service Information

    Bombardier-Rotax GmbH has issued Mandatory Service Bulletin (MSB) 
No. SB-912-022/SB-914-011, dated March, 2001, that specifies procedures 
for replacement of valve spring retainers P/N 854.182. The Austro 
Control classified this service bulletin as mandatory and issued AD No. 
108, in order to assure the airworthiness of these Bombardier-Rotax 
GmbH engines in Austria.

Bilateral Airworthiness Agreement

    This engine model is manufactured in Austria and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the Austro Control has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of the Austro Control, reviewed all available information, and 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.

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 Bombardier-Rotax GmbH 912 F, 912 S, and 914 F 
series reciprocating engines of the same type design, this AD is being 
issued to prevent cracking of the valve spring retainers resulting in 
possible engine failure while in-flight. This AD requires replacement 
of valve spring retainers, P/N 854.182, on engines with the single 
valve spring configuration, with new-reinforced valve spring retainers, 
P/N 854.184. The actions must be done in accordance with the service 
bulletin 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 2002-NE-17-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

[[Page 53475]]

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 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:

2002-16-07  Bombardier-Rotax GmbH: Amendment 39-12846. Docket No. 
2002-NE-17-AD.

Applicability

    This airworthiness directive (AD) is applicable to Bombardier-
Rotax GmbH type 912 F, 912 S, and 914 F series reciprocating engines 
with the serial numbers (SN's) in Table 1 of this AD, and all 
engines that have been converted to a single valve spring 
arrangement at engine repair or general overhaul. Table 1 follows:

                      Table 1.--Engine Series by SN
------------------------------------------------------------------------
                 Engine model                          Engine SN
------------------------------------------------------------------------
912 F........................................     4,412.757 to 4,412.794
                                                  4,412.796 to 4,412.807
912 S........................................     4,922.501 to 4,922.534
                                                  4,922.536 to 4,922.552
                                                  4,922.554 to 4,922.577
                                                  4,922.579 to 4,922.636
914 F........................................     4,420.039 to 4,420.048
                                                  4,420.050 to 4,420.067
                                                  4,420.069 to 4,420.082
                                                  4,420.084 to 4,420.097
                                                  4,420.099 to 4,420.114
                                                  4,420.116 to 4,420.155
                                                  4,420.157 to 4,420.253
------------------------------------------------------------------------

    These engines are installed on, but not limited to, Diamond 
Aircraft Industries, DA20-A1, Diamond Aircraft Industries GmbH Model 
HK 36 TTS, Model HK 36TTC, and Model HK 36 TTC-ECO, Iniziative 
Industriali Italiane S.p.A. Sky Arrow 650 TC and Sky Arrow 650 TCN, 
Aeromot-Industria Mecanico Metalurgica ltda., Models AMT-300 and 
AMT-200S, and Stemme S10-VT aircraft.

    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 (c) 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 cracking of the valve spring retainers resulting in 
possible engine failure while in-flight, do the following:

Replacement Procedure

    (a) Replace valve spring retainers part number (P/N) 854.182, of 
single valve spring configuration, with valve spring retainers P/N 
854.184, in accordance with 3.1.1 of the Accomplishment Instructions 
of Mandatory Service Bulletin (MSB) SB-912-022/SB-914-011, dated 
March, 2001, using the compliance times in the following Table 2:

                      Table 2.--Compliance Schedule
------------------------------------------------------------------------
 Engine flight hours (FH) on the effective
              date of this AD                          Replace
------------------------------------------------------------------------
(1) 0 FH (new engine).....................  Before installing on
                                             aircraft.
(2) 10 hours or less......................  Within 10 FH after the
                                             effective date of this AD.
(3) More than 10 but less than or equal to  Within 25 FH after the
 25 FH.                                      effective date of this AD.
(4) More than 25 FH.......................  Before exceeding 100 FH.
------------------------------------------------------------------------

    (b) For engines that have had the oil system accessed during 
repair or maintenance, replace the valve spring retainers in 
accordance with 3.1.1 of the Accomplishment Instructions of 
Mandatory Service Bulletin (MSB) SB-912-022/SB-914-011, dated March, 
2001, within 10 FH after the effective date of this AD.

Alternative Methods of Compliance

    (c) 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, Engine Certification Office (ECO). 
Operators must submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

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

Special Flight Permits

    (d) 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 aircraft to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (e) The replacements must be done in accordance with Bombardier-
Rotax GmbH Mandatory Service Bulletin (MSB) SB-912-022/SB-914-011, 
dated March, 2001. 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 Bombardier-
Rotax GmbH, Welser Strasse 32, A-4623 Gunskirchen, Austria; 
telephone 7246-601-232; fax 7246-601-370. Copies may be inspected 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.

    Note 3: The subject of this AD is addressed in Austro Control 
airworthiness directive No. 108.

Effective Date

    (f) This amendment becomes effective on September 3, 2002.

    Issued in Burlington, Massachusetts, on August 2, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20266 Filed 8-15-02; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:18:46.482796+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

d7bb18f92571a61325a98f7f49915d82186d63fe19da77baf0883bb6a7a8e998

Text SHA-256

bd747d0d3c0e252d2806246fc3f2339883e351bad5b56debfd3a73da00cf66ef