[Federal Register Volume 59, Number 102 (Friday, May 27, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-13012]
[[Page Unknown]]
[Federal Register: May 27, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-ANE-26]
Airworthiness Directives; Hamilton Standard 14RF, 247F, 14SF, and
6/5500/F Series Propellers
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to Hamilton Standard 14RF,
247F, 14SF, and 6/5500/F (formerly Hamilton Standard/British Aerospace
6/5500/F) series propellers, that currently requires initial and
repetitive inspections of the propeller control unit (PCU) servo
ballscrew internal spline (BIS) teeth for wear, and replacement, if
necessary, of PCU servo BIS assemblies. This action would increase the
repetitive inspection interval from 500 to 1,500 hours time in service
(TIS) since last inspection for propellers that have a ballscrew quill
damper installed. This proposal is prompted by the availability of
improved hardware that enhances the lubrication of the BIS and
significantly reduces BIS wear. The actions specified by the proposed
AD are intended to prevent inability to control the propeller blade
angle due to tooth wear in the PCU servo BIS assembly.
DATES: Comments must be received by June 27, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 94-ANE-26, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at
this location between 8 a.m. and 4:30 p.m., Monday through Friday,
except Federal holidays.
The service information referenced in the proposed rule may be
obtained from Hamilton Standard, One Hamilton Road, Windsor Locks, CT
06096-1010. This information may be examined at the FAA, New England
Region, Office of the Assistant Chief Counsel, 12 New England Executive
Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (617) 238-7158, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal 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 94-ANE-26.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 94-ANE-26, 12 New England Executive Park,
Burlington, MA 01803-5299.
Discussion
On August 13, 1993, the Federal Aviation Administration (FAA)
issued airworthiness directive (AD) 93-16-02, Amendment 39-8659 (58 FR
44441, August 23, 1993), to require initial and repetitive inspections
of the propeller control unit (PCU) servo ballscrew internal spline
(BIS) teeth for wear, and replacement, if necessary, of PCU servo BIS
assemblies. That action was prompted by a report of an incident where
the crew experienced difficulties in feathering and controlling the
propeller blade angle. Investigation of the PCU servo BIS assembly
revealed excessively worn spline teeth. That condition, if not
corrected, could result in inability to control the propeller blade
angle due to tooth wear in the PCU servo BIS assembly.
Since the issuance of that AD, Hamilton Standard has developed a
damper to be installed between the end of the ballscrew and the
shoulder of the quill shaft. The damper preloads the quill against the
retaining ring and eliminates axial motion between the quill and the
ballscrew. This reduces vibration, enhances ballscrew lubrication, and
results in an extension of the useful life of the BIS assembly.
In addition, the manufacturer has issued revisions to the alert
service bulletins (ASB) referenced in the current AD. The FAA has
reviewed and approved the technical contents of the following Hamilton
Standard ASB's, all dated April 7, 1994: No. 14SF-61-A59, Revision 4;
No. 14RF-9-61-A53, Revision 5; No. 14RF-19-61-A25, Revision 4; No.
14RF-21-61-A38, Revision 4; No. 247F-61-A3, Revision 3; and No. 6/5500/
F-61-A11, Revision 4. These revisions enable affected propellers with a
ballscrew quill damper installed in accordance with the following
Hamilton Standard SB's to extend the repetitive inspection interval
from 500 to 1,500 hours time in service (TIS) since last inspection:
No. 14SF-61-67, Revision 1, dated May 6, 1994; No. 14RF-9-61-61, dated
December 9, 1993; No. 14RF-19-61-29, Revision 1, dated May 6, 1994; No.
14RF-21-61-48, Revision 1, dated May 6, 1994; No. 247F-61-6, Revision
1, dated May 6, 1994; and No. 6/5500/F-61-19, Revision 1, dated May 6,
1994.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 93-16-02 to increase the repetitive
inspection interval from 500 to 1,500 hours TIS since last inspection
for propellers that have a ballscrew quill damper installed.
There are approximately 2,506 propellers of the affected design in
the worldwide fleet. The FAA estimates that 1150 propellers installed
on aircraft of U.S. registry would be affected by this proposed AD,
that it would take approximately 1.5 work hours per engine to
accomplish the proposed actions, and that the average labor rate is $55
per work hour. Based on these figures, and on the average utilization
rate of 2,000 hours TIS per year equating to 4 inspections, the total
cost impact of the proposed AD per inspection on U.S. operators is
estimated to be $379,500. However, based on an average utilization rate
of 2,000 hours TIS per year, the proposed AD would eliminate 2.7
inspections per year per propeller, resulting in an approximate yearly
cost savings to U.S. operators of $256,163.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting 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.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-8659 (58 FR
44441, August 23, 1993) and by adding a new airworthiness directive to
read as follows:
Hamilton Standard: Docket No. 94-ANE-26. Supersedes AD 93-16-02,
Amendment 39-8659.
Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF-
21, and 14RF-23; 247F-1; 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15,
14SF-17, 14SF-19, 14SF-23; and 6/5500/F propellers installed on but
not limited to Embraer EMB-120 and EMB-120RT; SAAB-SCANIA SF340B;
Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72, ATR72-210;
DeHavilland DHC-8-100 series, DHC-8-300; Construcciones Aeronauticas
SA (CASA) CN-235 and CN-235-100; Canadair CL215T and CL415; and
British Aerospace ATP airplanes.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the inability to control the propeller blade angle
due to tooth wear in the propeller control unit (PCU) servo
ballscrew internal spline (BIS) assembly, accomplish the following:
(a) Inspect the PCU servo BIS assembly for tooth wear in
accordance with the Accomplishment Instructions of the following
Hamilton Standard Alert Service Bulletins (ASB), all dated April 7,
1994, as applicable: No. 14RF-9-61-A53, Revision 5; No. 14RF-19-61-
A25, Revision 4; No. 14RF-21-61-A38, Revision 4; No. 247F-61-A3,
Revision 3; No. 14SF-61-A59, Revision 4; and No. 6/5500/F-61-A11,
Revision 4; as follows:
(1) For a PCU with unknown time in service (TIS), and unknown
TIS since the last inspection, on the effective date of this
airworthiness directive (AD), and that does not have a ballscrew
quill damper installed, inspect within 200 hours TIS after the
effective date of this AD.
(2) For a PCU with 1,800 or more hours TIS or unknown TIS on the
effective date of this AD, and either has not been inspected, or has
been inspected more than 500 hours prior to the effective date of
this AD, in accordance with the applicable Hamilton Standard ASB
listed in paragraph (a) of this AD; and that does not have a
ballscrew quill damper installed; inspect within 200 hours TIS after
the effective date of this AD.
(3) For a PCU with 1,800 or more hours TIS or unknown TIS on the
effective date of this AD, and that has been inspected within the
previous 500 hours TIS in accordance with the applicable Hamilton
Standard ASB listed in paragraph (a) of this AD, and that does not
have a ballscrew quill damper installed, inspect within 500 hours
TIS since the last inspection in accordance with the applicable
Hamilton Standard ASB listed in paragraph (a) of this AD.
(4) For a PCU with less than 1,800 hours TIS on the effective
date of this AD, and that does not have a ballscrew quill damper
installed, inspect prior to accumulating 1,800 hours TIS, or within
300 hours TIS after the effective date of this AD, whichever occurs
later.
(5) For a PCU that has a ballscrew quill damper installed in
accordance with the following applicable Hamilton Standard Service
Bulletins (SB), or previous revisions: No. 14SF-61-67, Revision 1,
dated May 6, 1994; No. 14RF-9-61-61, dated December 9, 1993; No.
14RF-19-61-29, Revision 1, dated May 6, 1994; No. 14RF-21-61-48,
Revision 1, dated May 6, 1994; No. 247F-61-6, Revision 1, dated May
6, 1994; and No. 6/5500/F-61-19, Revision 1, dated May 6, 1994;
inspect within 1,500 hours TIS since installation of the ballscrew
quill damper.
(6) Thereafter, inspect at intervals described as follows:
(i) For propellers that have a ballscrew quill damper installed
in accordance with the applicable Hamilton Standard SB listed in
paragraph (a)(5) of this AD, or previous revisions, inspect at
intervals not to exceed 1,500 hours TIS since the last inspection
required by this AD.
(ii) For propellers that do not have a ballscrew quill damper
installed in accordance with the applicable Hamilton Standard SB
listed in paragraph (a)(5) of this AD, inspect at intervals not to
exceed 500 hours TIS since the last inspection required by this AD.
(7) If PCU servo BIS teeth are worn beyond the limits specified
in the Accomplishment Instructions of the applicable ASB's listed in
paragraph (a) of this AD, prior to further flight, replace the PCU
with a serviceable assembly in accordance with the Acccomplishment
Instructions of the applicable ASB's listed in paragraph (a) of this
AD, and thereafter reinspect in accordance with paragraphs (a)(6)
and (a)(7) of this AD.
(b) Report the results of the initial and repetitive inspections
required by paragraph (a) of this AD by utilizing Appendix 1,
``Ballscrew Inspection Data,'' within 7 days of the inspection to
the Manager, Boston Aircraft Certification Office, Engine and
Propeller Directorate, Aircraft Certification Service, FAA, 12 New
England Executive Park, Burlington, MA 01803-5299; Telex Number
949301 FAAANE BURL; fax (617) 238-7199. The reporting requirements
of this AD terminate on December 31, 1994. Information collection
requirements contained in this regulation have been approved by the
Office of Management and Budget (OMB) under the provision of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have
been assigned OMB Control Number 2120-0056.
Appendix 1
Ballscrew Inspection Data
The following information must be reported and sent as soon as
possible but no later than 7 days after inspection to: Manager,
Boston Aircraft Certification Office, Engine and Propeller
Directorate, Aircraft Certification Service, Federal Aviation
Administration, 12 New England Executive Park, Burlington, MA 01803-
5299, Fax: (617) 238-7199.
Operator/Repair
Station----------------------------------------------------------------
Date of
Inspection-------------------------------------------------------------
PCU Part
Number-----------------------------------------------------------------
PCU Serial
Number-----------------------------------------------------------------
Date Damper
Installed--------------------------------------------------------------
Aircraft Model---------------------------------------------------------
Aircraft Serial
Number-----------------------------------------------------------------
Position:
Left Engine------------------------------------------------------------
Right Engine-----------------------------------------------------------
(please check)
(please circle):
Estimated Time On PCU--------------------------------------------------
Actual Time On PCU-----------------------------------------------------
Time Since New (Hours) ________
Time Since Last Ballscrew Inspection/Repair (Hours) ________
Inspection:
Accepted---------------------------------------------------------------
*Rejected--------------------------------------------------------------
*Please indicate in comments if unit was rejected as part of the
functional check.
No. of left side teeth with steps ________
No. of right side teeth with steps ________
Comments:--------------------------------------------------------------
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(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, Boston Aircraft Certification
Office. The request should be forwarded through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Boston Aircraft Certification Office.
Note: 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.
(d) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the aircraft to a location where
the requirements of this AD can be accomplished.
Issued in Burlington, Massachusetts, on May 19, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 94-13012 Filed 5-26-94; 8:45 am]
BILLING CODE 4910-13-P