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

[Federal Register Volume 67, Number 158 (Thursday, August 15, 2002)]
[Rules and Regulations]
[Pages 53296-53299]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20679]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-08-AD; Amendment 39-12865; AD 2002-16-26]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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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 and 914 F series reciprocating engines. This action requires 
initial and repetitive visual inspections of the engine crankcase for 
cracks. This amendment is prompted by reports of several instances of 
engine crankcases found cracked in service. The actions specified in 
this AD are intended to prevent oil loss caused by cracks in the engine 
crankcase, which could lead to in-flight failure of the engine and 
forced landing.

DATES: Effective September 16, 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-08-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. 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.

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, recently notified the FAA that an unsafe 
condition may exist on certain SN's of Bombardier-Rotax GmbH type 912 F 
and 914 F series reciprocating engines. Austro Control advises that 
reports have been received of three engine crankcases found cracked in 
service. To date, there have been no engine failures due to cracks in 
the crankcase. However, Austro Control has determined that an engine 
could fail due to oil loss from a cracked crankcase. This condition, if 
not corrected, could result in an inflight failure of the engine and 
forced landing.

Bilateral Airworthiness Agreement

    Bombardier-Rotax GmbH type 912 F and 914 F series reciprocating 
engines are manufactured in Austria and are 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, Austro Control has kept the FAA informed of 
the situation described above. The FAA has examined the findings of 
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 type 912 F and 914 F 
series reciprocating engines of the same type design, this AD is being 
issued to prevent oil loss caused by cracks in the engine crankcase, 
which could lead to in-flight failure of the engine and forced landing. 
This AD requires initial visual inspection for cracks of the engine 
crankcase of certain SN engines, within 50 hours time-in-service (TIS) 
after the effective date of this AD, and repetitive visual inspections 
at each 100-hour, annual, or progressive inspection, or within 110 
hours TIS since last inspection, whichever occurs first. If any cracks 
are found the engine must be replaced with a serviceable engine. The 
SN's affected are, for 912 F series engines, SN's 4,412.796 or lower, 
and for 914 F series engines, SN's 4,420.313 or lower. Examples of 
lower SN's are 4,412.795, 4,412.794, and 4,412.793, and 4,420.312, 
4,420.311, and 4,420.310.

Immediate Adoption of This AD

    Since a situation exists that requires the immediate adoption of 
this

[[Page 53297]]

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-08-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 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, 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:

2002-16-26  Bombardier-Rotax GmbH: Amendment 39-12865. Docket No. 
2002-NE-08-AD.

Applicability

    This airworthiness directive (AD) is applicable to Bombardier-
Rotax GmbH type 912 F series reciprocating engines serial number 
(SN) 4,412.796, or lower, and 914 F series reciprocating engines SN 
4,420.313, or lower. These engines are installed on, but not limited 
to, Aeromot-Industria Mecanico Metalurgica Itda. model AMT-300, 
Diamond Aircraft Industries DA20-A1, Diamond Aircraft Industries 
GmbH Model HK 36 TTS, Iniziative Industriali Italiane S.p.A. Sky 
Arrow 650 series, and Stemme S10-VT aircraft.

    Note 1: Examples of lower SN's are 4,412.795, 4,412.794, and 
4,412.793, and 4,420.312, 4,420.311, and 4,420.310.


    Note 2: 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 oil loss caused by cracks in the engine crankcase, 
which could lead to in-flight failure of the engine and forced 
landing, do the following:

Initial Inspection

    (a) Within 50 hours time-in-service (TIS) from the effective 
date of this AD, perform a visual inspection as follows:
    (1) Inspect the engine crankcase (item 1, Figure 1 of this AD) 
for cracks especially in the area of cylinder 1 upper side (item 2), 
between cylinder 1 and 3 upper side (item 3), and cylinder 4 lower 
side (item 4).

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[GRAPHIC] [TIFF OMITTED] TR15AU02.000

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    (2) Cracks in crankcases of engines with a ROTAX cooling air 
baffle may not be easily visible, and oil leaks may be an indication 
of cracks. Visually inspect for oil leaks in areas of (item 2) and 
(item 3).
    (3) If oil leaks are found, determine the source by either using 
a borescope or removing the object blocking the view such as the air 
baffle or accessory, and perform the inspection.
    (4) If the engine crankcase is cracked, replace engine before 
further flight. Repair oil leaks from any other cause.

    Note 3: Information concerning this inspection can be found in 
Bombardier-Rotax mandatory service bulletins No's. SB-912-029, dated 
May 2001/SB-914-018, Revision 1, dated December 2001.

Repetitive Inspections

    (b) Visually inspect the engine crankcase (item 1, Figure 1 of 
this AD) for cracks at each 100-hour, annual, or progressive 
inspection, or within 110 hours TIS since last inspection, whichever 
occurs first, in accordance with paragraph (a) 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 4: 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.

    Note 5: The subject of this AD is addressed in Austro Control 
airworthiness directive No. 107 R1, dated December 1, 2001.

Effective Date

    (e) This amendment becomes effective on August 30, 2002.

    Issued in Burlington, Massachusetts, on August 7, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20679 Filed 8-14-02; 8:45 am]
BILLING CODE 4910-13-P

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