[Federal Register Volume 62, Number 162 (Thursday, August 21, 1997)]
[Rules and Regulations]
[Pages 44404-44406]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-22146]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-73-AD; Amendment 39-10111; AD 97-17-08]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Model 1900D
Airplanes (Formerly Known as Beech Aircraft Corporation Model 1900D
Airplanes)
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 Raytheon Aircraft Company (Raytheon) Model 1900D
airplanes (formerly known as Beech Aircraft Corporation Model 1900D
airplanes) that have not had the propeller removed and re-installed
since factory installation. This action requires inspecting the
propeller mounting bolts for the proper torque and replacing or re-
torquing any propeller bolt with the wrong torque level. The
manufacturer discovered some under-torqued propeller mounting bolts
during factory installation of the propeller. The actions specified by
this AD are intended to prevent fatigue cracking and failure of the
propeller mounting bolts, which if not detected and corrected, could
result in loss of the propeller.
DATES: Effective September 24, 1997.
Comments for inclusion in the rules docket must be received on or
before October 30, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 97-CE-73-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
Raytheon Aircraft Company, 9709 E. Central, P.O. Box 85, Wichita,
Kansas 67201-0085. This information may also be examined at the Federal
Aviation Administration (FAA), Central Region, Office of the Assistant
Chief Counsel, Attention: Rules Docket 97-CE-73-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106.
FOR FURTHER INFORMATION CONTACT: Mr. Randy Griffith, Aerospace
Engineer, Wichita Aircraft Certification Office, Room 100, 1801 Airport
Rd., Wichita, Kansas 67209; telephone (316) 946-4145; facsimile (316)
946-4407.
[[Page 44405]]
SUPPLEMENTARY INFORMATION:
Discussion
The FAA has received three reports from operators and has recently
been notified by Raytheon Aircraft Company (Raytheon) (formerly known
as Beech Aircraft Corporation) that certain Raytheon Model 1900D
airplane propellers were inadvertently installed with under-torqued
propeller mounting bolts at factory installation. The bolts were not
being torqued to the end torque requirement of 100 to 105 ft-lbs. These
bolts have a three stage, wet torque requirement ending at a value of
100 to 105 ft-lbs. Originally it was believed that the bolts were being
torqued to at least 80 ft-lbs (the second stage of the torque
procedure), but three cases of bolts with less than 60 ft-lbs have been
reported. The manufacturer of the propeller and Raytheon notified the
owners/operators of the affected Model 1900D airplanes (serial numbers
(S/N) UE-176 through UE-280, UE-282 and UE-284) by ``urgent action''
letter. If the propeller bolts are not torqued to the right level,
fatigue cracking could result.
Relevant Service Information
Raytheon has issued an urgent action Letter No. 52-0092, dated July
22, 1997, which references the propeller bolt torque problem and the
recommended action to fix the torque levels.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
relevant service information, the FAA has determined that AD action
should be taken to prevent fatigue cracking and failure of the
propeller mounting bolts, which if not detected and corrected, could
result in loss of the propeller.
Explanation of the Provisions of the AD
Since an unsafe condition has been identified that is likely to
exist or develop in certain Raytheon Model 1900D airplanes of the same
type design that have not had the propeller removed and re-installed,
this AD requires inspecting the propeller mounting bolts for correct
torque level, and re-torquing or replacing the bolts as necessary.
Determination of the Effective Date of the AD
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for public
prior 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 immediate flight safety and, thus, was not
preceded by notice and opportunity to 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 above. 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 rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-CE-73-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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 (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the rules
docket.
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 a new airworthiness directive
(AD) to read as follows:
97-17-08. Raytheon Aircraft Company: Amendment 39-10111; Docket No.
97-CE-73-AD.
Applicability: Model 1900D airplanes (serial numbers UE-176
through UE-280, UE-282 and UE-284) certificated in any category,
that have not had the propeller removed and re-installed since
factory installation, or have not had the attaching bolts re-
torqued.
Note 1: This AD applies to each airplane 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 airplanes 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: Required within the next 50 hours time-in-service
(TIS), unless already accomplished (accomplished according to
Raytheon Aircraft Company Letter No. 52-0092, dated July 22, 1997).
To prevent fatigue cracking and failure of the propeller
mounting bolts, which if not detected and corrected, could result in
loss of the propeller, accomplish the following:
[[Page 44406]]
(a) Accomplish the following if the airplane records indicate
that the propeller has not been removed and re-installed since the
factory installation.
(1) Remove spinner dome, cowling, and hardware as required to
access propeller attachment bolts.
(2) Reposition the beta system, using beta positioning tool, and
remove the safety wire from the propeller mounting bolts (part
number (P/N) B3347).
(3) Check the torque level of the P/N B3347 propeller bolts.
(i) If the torque is less than 60 ft-lbs, prior to further
flight, replace the bolts with another FAA-approved propeller bolt
using the installation procedures and torque sequence detailed in
the Model 1900D Maintenance Manual (61-10-00) (A/Steps 1, 2, and B/
Step 3).
(ii) If torque is 60 ft-lbs or greater, torque the bolts to a
value of 100-105 ft-lbs using the torque sequence detailed in the
Model 1900D Maintenance Manual (61-10-00) (B/Step 3).
(4) Re-safety wire the propeller bolts and remove the beta
system positioning tool.
(5) Re-install the hardware, the spinner, and the cowlings.
(b) 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 requirements of this AD can be accomplished.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Wichita Aircraft Certification Office, Room
100, 1801 Airport Rd., Wichita, Kansas 67209. The request shall be
forwarded through an appropriate FAA Maintenance Inspector, who may
add comments and then send it to the Manager, Wichita Aircraft
Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from Wichita Aircraft Certification Office.
(d) Information related to this AD may be inspected at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri 64106.
(e) This amendment (39-10111) becomes effective on September 24,
1997.
Issued in Kansas City, Missouri, on August 14, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-22146 Filed 8-20-97; 8:45 am]
BILLING CODE 4910-13-U
