[Federal Register Volume 64, Number 130 (Thursday, July 8, 1999)]
[Rules and Regulations]
[Pages 36777-36779]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-16745]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NE-35-AD; Amendment 39-11216; AD 99-14-06]
RIN 2120-AA64
Airworthiness Directives; MT-Propeller Entwicklung GMBH Models
MTV-9-B-C and MTV-3-B-C Propellers
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 MT-Propeller Entwicklung GMBH Models MTV-9-B-C and
MTV-3-B-C propellers. This action requires initial and repetitive
inspections of Torx head blade root lag screws for torque values and
breakage, and, if any screws are found broken or with insufficient
torque, replacement of all screws with new lag screws. In addition,
this AD requires replacement of certain model Torx head blade root lag
screws with improved, hexagonal head blade root lag screws. This
amendment is prompted by reports of broken Torx head blade root lag
screws. The actions specified in this AD are intended to prevent blade
root lag screw breakage, which could result in propeller blade
separation and loss of control of the airplane.
DATES: Effective July 23, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 23, 1999.
Comments for inclusion in the Rules Docket must be received on or
before September 7, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 99-NE-35-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9-ane-
[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
MT-Propeller Entwicklung GMBH, Airport Straubing-Wallmuhle, D-94348
Atting, Germany; telephone (0 94 29) 84 33, fax (0 94 29) 84 32,
Internet: ``[email protected]''. This information may be examined 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: Wayne E. Gaulzetti, Aerospace
Engineer, Boston Aircraft Certification Office, FAA, Engine and
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803-5299; telephone (781) 238-7156, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Luftfahrt-Bundesamt (LBA), which is the
airworthiness authority for Germany, recently notified the Federal
Aviation Administration (FAA) that an unsafe condition may exist on MT-
Propeller Entwicklung GMBH Models MTV-9-B-C and MTV-3-B-C propellers.
The LBA advises that they have received reports of broken Torx head
blade root lag screws found during routine teardowns. The investigation
revealed that the screws broke due to insufficient torque. This
condition, if not corrected, could result in blade root lag screw
breakage, which could result in propeller blade separation and loss of
control of the airplane.
MT-Propeller Entwicklung GMBH has issued Service Bulletin (SB) No.
17-A, dated March 5, 1999, that specifies procedures for inspections
for Torx head blade root lag screws for torque values and breakage, and
replacement of Torx head blade root lag screws, part number (P/N) A-
550-85 (4mm thread pitch), with improved, hexagonal head blade root lag
screws, P/N A-983-85. The LBA classified this SB as mandatory and
issued airworthiness directives (ADs) 1999-081/2 and 1999-082/2 in
order to assure the airworthiness of these propellers in Germany.
This propeller model is manufactured in Germany and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the LBA has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
LBA, 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.
Since an unsafe condition has been identified that is likely to
exist or develop on other propellers of the same type design registered
in the United States, the AD requires initial and repetitive
inspections of Torx head blade root lag screws for torque values and
breakage, and, if any screws are found with insufficient torque or are
broken, replacement of all screws with new lag screws. In addition,
this AD requires replacement of Torx head blade root lag screws, P/N A-
550-85 (4mm thread pitch), with improved, hexagonal head blade root lag
screws, P/N A-983-85. The actions would be required to be accomplished
in accordance with the SB described previously.
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
[[Page 36778]]
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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NE-35-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
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, 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:
99-14-06 MT-Propeller Entwicklung GMBH: Amendment 39-11216. Docket
99-NE-35-AD.
Applicability: MT-Propeller Entwicklung GMBH Model MTV-9-B-C
propellers with serial numbers (S/Ns) starting with 98 or less,
equipped with CL250-27 or CL260-27 blades with S/Ns starting with
letter ``A'' through ``P'', equipped with Torx head blade root lag
screws, P/N A-549-85 (3mm thread pitch), or P/N A-550-85 (4mm thread
pitch); and Model MTV-3-B-C propellers with S/Ns starting with 98 or
less, equipped with L250-21 blades with S/Ns starting with letter
``A'' through ``P'', equipped with Torx head blade root lag screws,
P/N A-549-85 (3mm thread pitch), or A-550-85 (4mm thread pitch).
These propellers are installed on but not limited to Sukhoi SU-26,
SU-29, SU-31; Yakovlev YAK-52, YAK-54, YAK-55, and Technoavia SM-92
airplanes.
Note 1: This airworthiness directive (AD) applies to each
propeller 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 propellers 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 blade root lag screw breakage, which could result in
propeller blade separation and loss of control of the airplane,
accomplish the following:
(a) For propellers with Torx head blade root lag screws, P/N A-
549-85 (3mm thread pitch), perform initial and repetitive
inspections of Torx head blade root lag screws for torque values and
breakage, and, if necessary, replace with new lag screws, in
accordance with MT-Propeller Entwicklung GMBH Service Bulletin (SB)
No. 17-A, dated March 5,1999, as follows:
(1) Initially inspect within 50 hours time-in-service (TIS), or
within 2 months after the effective date of this AD, whichever
occurs first.
(2) Thereafter, inspect at intervals not to exceed 100 hours
TIS, or within 12 months, whichever occurs first.
(3) Prior to further flight, if any Torx head blade root lag
screws are found broken or with torque less than 64 foot-pounds,
replace all Torx head blade root lag screws with new lag screws.
(b) For propellers with Torx head blade root lag screws, P/N A-
550-85 (4mm thread pitch), perform a one-time inspection of Torx
head blade root lag screws for torque values and breakage, and, if
necessary, replace with lag screws, in accordance with MT-Propeller
Entwicklung GMBH SB No. 17-A, dated March 5,1999, as follows:
(1) Inspect within 50 hours TIS, or within 2 months after the
effective date of this AD, whichever occurs first.
(2) Prior to further flight, if any Torx head blade root lag
screws are found broken or with torque less than 64 foot-pounds,
replace all Torx head blade root lag screws with improved, hexagonal
head blade root lag screws, P/N A-983-85.
(c) For propellers with Torx head blade root lag screws, P/N A-
550-85 (4mm thread pitch), within 100 hours TIS, or within 12 months
after the effective date of this AD, replace all Torx head blade
root lag screws, P/N A-550-85, with improved, hexagonal head blade
root lag screws, P/N A-983-85, in accordance with MT-Propeller
Entwicklung GMBH SB No. 17-A, dated March 5,1999.
(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, Boston Aircraft Certification
Office. Operators shall submit their requests through an appropriate
FAA Maintenance Inspector, who may add comments and then send it to
the Manager, Boston 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 Boston 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 airplane to a location where
the inspection requirements of this AD can be accomplished.
(f) The actions required by this AD shall be performed in
accordance with the following MT-Propeller Entwicklung GMBH SB:
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Document No. Pages Date
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17-A.................................. 1-3 March 5, 1999
Total pages: 3.
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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 MT-Propeller Entwicklung GMBH,
Airport Straubing-Wallmuhle, D-94348 Atting, Germany; telephone (0
94 29) 84 33, fax (0 94 29) 84 32, Internet: ``[email protected]''.
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.
(g) This amendment becomes effective on July 23, 1999.
[[Page 36779]]
Issued in Burlington, Massachusetts, on June 23, 1999.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 99-16745 Filed 7-7-99; 8:45 am]
BILLING CODE 4910-13-U