Document ID: FAA-2010-0342-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier-Rotax GmbH Type 912 F, 912 S, and 914 F Series Reciprocating Engines
Posted Date: 2010-10-04T04:00Z

[Federal Register: October 4, 2010 (Volume 75, Number 191)]
[Rules and Regulations]               
[Page 61046-61050]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04oc10-2]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0342; Directorate Identifier 2002-NE-08-AD; 
Amendment 39-16458; AD 2010-20-23]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for certain serial numbers (S/Ns) of Bombardier-Rotax GmbH type 
912 F and 914 F series reciprocating engines. That AD currently 
requires initial and repetitive visual inspections of the engine 
crankcase for cracks. This AD requires those same inspections, adds the 
912 S series to the affected population, adds a test procedure to 
determine the engine suitability for a special flight permit, and 
changes applicability from engine S/N to crankcase S/N. This AD results 
from an increase in the affected crankcase population. We are issuing 
this AD 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: This AD becomes effective November 8, 2010.

ADDRESSES: You can get the service information identified in this AD 
from BRP-Rotax GmbH & Co. KG, Welser Strasse 32, A-4623 Gunskirchen, 
Austria.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
alan.strom@faa.gov; telephone (781) 238-7143; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2002-16-26, Amendment 39-12865 (67 FR 53296, August 15, 
2002), with a proposed AD. The proposed AD applies to Bombardier-Rotax 
GmbH type 912 F, 912 S, and 914 F series reciprocating engines with 
certain serial-numbered crankcases. We published the proposed AD in the 
Federal Register on April 7, 2010 (75 FR 17632). That action proposed 
to require initial visual inspection for cracks in the engine crankcase 
of engines with certain serial-numbered crankcases, within 50 hours 
time-in-service (TIS) after the effective date of that 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 removed from 
service.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.
    One commenter asks us to change paragraph (g)(4) from ``If the 
engine crankcase is cracked, replace the engine before further flight'' 
to ``If the engine crankcase is cracked, replace, repair, or overhaul 
the engine before further flight''. The commenter states that this 
would allow the option of replacing the crankcase as a repair or 
overhaul as well as an outright engine replacement.
    We partially agree. An owner or operator might interpret paragraph 
(g)(4) to mean they can't repair the engine. We have changed paragraph 
(g)(4) to state ``If the engine crankcase is cracked, remove the engine 
from service before further flight.''

[[Page 61047]]

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the change described previously. 
We have determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 250 products of U.S. registry. We also estimate that it 
will take about 3 work-hours per inspection and 20 work hours to 
replace the crankcase to comply with this AD. The average labor rate is 
$85 per work-hour. Required parts will cost about $6,500 per crankcase. 
Based on these figures and an estimate of one crankcase replaced per 
year, we estimate the annual cost of the AD on U.S. operators to be 
$71,950. Our cost estimate is exclusive of possible warranty coverage.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    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 this AD:
    (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.
    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 at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-12865 (67 FR 
53296, August 15, 2002), and by adding a new airworthiness directive, 
Amendment 39-16458, to read as follows:

2010-20-23 Bombardier-Rotax GmbH (formerly Rotax, Motorenfabrik): 
Amendment 39-16458. Docket No. FAA-2010-0342; Directorate Identifier 
2002-NE-08-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
8, 2010.

Affected ADs

    (b) This AD supersedes AD 2002-16-26, Amendment 39-12865.

Applicability

    (c) This AD is applicable to Bombardier-Rotax GmbH type 912 F 
series, 912 S series, and 914 F series reciprocating engines that 
have a crankcase serial-numbered 27811 or lower, installed. These 
engines are installed on, but not limited to, Aeromot-Industria 
Mecanico Metalurgica Itda AMT-300; Aquila Technische Entwiklugen 
GmbH AQUILA AT01; Diamond Aircraft Industries DA-20A1; Diamond 
Aircraft Industries GmbH Models HK36TC, HK36TTC, HK36TTC-ECO, and 
HK36TTS; Iniziative Industriali Italiane S.p.A. Sky Arrow 650 
series; SCHEIBE-Flugzeugnau GmbH SF 25C; and Stemme S10-VT aircraft.

Unsafe Condition

    (d) This AD results from an increase in the affected engine 
crankcase population. We are issuing this AD to prevent oil loss 
caused by cracks in the engine crankcase, which could lead to in-
flight failure of the engine and forced landing.

Compliance

    (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.

Determining the Crankcase Serial Number (S/N)

    (f) Determine if your crankcase is affected by looking at the S/
N in the area indicated by XXX, following ``Made in Austria,'' as 
shown on Figure 2 of this AD. The marking is on both crankcase 
halves.

Initial Inspection

    (g) 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), cylinder 4 lower-right 
side (item 4) and detailed inspection in the area identified in 
Figure 2 (item 5) of this AD. Information concerning this inspection 
can be found in Bombardier-Rotax Mandatory Service Bulletins No. SB-
912-029, Revision 3, dated July 11, 2006 and No. SB-914-018, 
Revision 3, dated July 11, 2006.
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[[Page 61049]]

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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 cylinder 1 
upper side (item 2, Figure 1 of this AD) and between cylinder 1 and 
cylinder 3 upper side (item 3).
    (3) If you find oil leaks, 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, remove the engine from 
service before further flight.

Repetitive Inspections

    (h) 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 paragraphs (g)(1) through (g)(4) of 
this AD.

Alternative Methods of Compliance

    (i) The Manager, Engine 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.

Special Flight Permits

    (j) Under 14 CFR part 39.23, we are limiting the special flight 
permits for this AD by the following conditions if the crankcase is 
cracked or there is evidence of oil leakage from the crankcase:
    (1) Perform a leak check as follows:
    (i) Clean the crankcase surface to remove any oil.
    (ii) Warm up the engine to a minimum oil temperature of 50 
degrees C (120 degrees F). Information about warming up the engine 
can be found in the applicable line maintenance manual.
    (iii) Accelerate the engine to full throttle and stabilize at 
full throttle speed for a time period of 5 to 10 seconds. 
Information about performing a full throttle run can be found in the 
applicable line maintenance manual.
    (iv) Shutdown after running the engine at idle only long enough 
to prevent vapor locks in the cooling system and fuel system.
    (v) Inspect the crankcase for evidence of oil leakage. Oil 
wetting is permitted, but oil leakage of more than one drip in 3 
minutes after engine shutdown is not allowed.
    (2) Check the crankcase mean pressure to confirm that it is 1.46 
pounds-per-square inch gage (psig) (0.1 bar) or higher when checked 
at takeoff power to ensure proper return of oil from the crankcase 
to the oil tank. Information about checking crankcase mean pressure 
is available in the Lubrication System section of the applicable 
engine installation manual.
    (3) A ferry flight is not allowed if oil leakage exceeds one 
drip in 3 minutes or if crankcase mean pressure is below 1.46 psig.

Optional Terminating Action

    (k) Installing a crankcase that has a S/N above 27811 terminates 
the inspection requirements of paragraphs (g)(1) through (g)(4) and 
(h) of this AD.

[[Page 61050]]

Related Information

    (l) Contact Alan Strom, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; 
telephone (781) 238-7143; fax (781) 238-7199, for more information 
about this AD.
    (m) EASA airworthiness directive 2007-0025, dated February 1, 
2007, also addresses the subject of this AD.
    (n) Bombardier-Rotax Mandatory Service Bulletins No. SB-912-029, 
Revision 3, dated July 11, 2006 and No. SB-914-018, Revision 3, 
dated July 11, 2006, pertain to the subject of this AD. Contact BRP-
Rotax GmbH & Co. KG, Welser Strasse 32, A-4623 Gunskirchen, Austria, 
or go to rotax-aircraft-engines.com for a copy of this service 
information.

Material Incorporated by Reference

    (o) None.

    Issued in Burlington, Massachusetts, on September 24, 2010.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-24629 Filed 10-1-10; 8:45 am]
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