[Federal Register Volume 61, Number 80 (Wednesday, April 24, 1996)]
[Rules and Regulations]
[Pages 18052-18058]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-9806]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-ANE-05; Amendment 39-9568; AD 96-08-02]
Airworthiness Directives; Hamilton Standard Models 14RF-9, 14RF-
19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17,
14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F
Propellers
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Hamilton Standard Models 14RF-9, 14RF-19, 14RF-21;
and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and
14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propellers,
that currently requires that all blades of applicable Hamilton Standard
propellers be calibrated for ultrasonic transmissibility before
conducting the ultrasonic shear wave inspection. In addition, that AD
decreases the repetitive inspection interval for the Hamilton Standard
Models 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 propellers from
1,250 flight cycles to 500 flight cycles. That AD also establishes a
new ultrasonic shear wave inspection interval of 1,000 flight cycles
for the Hamilton Standard Model 14RF-19, and 2,500 flight cycles for
the Hamilton Standard Model 14RF-21 and Hamilton Standard/British
Aerospace Model 6/5500/F. Also, that AD removes Hamilton Standard Model
14SFL11 propellers from service. This amendment requires a blade repair
that constitutes terminating action to the repetitive ultrasonic taper
bore inspections. Repetitive ultrasonic taper bore inspections are
required until the blade is repaired in accordance with this AD. This
amendment is prompted by the development of a taper bore repair process
that removes the damaged material and returns the blade to a condition
that does not require repetitive ultrasonic taper bore inspections. The
actions specified by this AD are intended to prevent separation of a
propeller blade due to cracks initiating in the blade taper bore, that
can result in aircraft damage, and possible loss of aircraft control.
DATES: Effective May 9, 1996.
The incorporation by reference of Hamilton Standard Alert Service
Bulletins (ASB's): No. 14RF-9-61-A91, No. 14RF-19-61-A55, No. 14RF-21-
61-A73, No. 14SF-61-A93, and No. 6/5500/F-61-A41, all dated December 7,
1995, and Hamilton Standard ASB's No. 14RF-9-61-A91, Revision 1, No.
14RF-19-61-A55, Revision 1, No. 14RF-21-61-A73, and Revision 1, No.
14SF-61-A93, all dated December 15, 1995, and No. 6/5500/F-61-A41,
Revision 1, dated December 18, 1995; and Hamilton Standard ASB's No.
14RF-9-61-A95, No. 14RF-19-61-A57, No. 14RF-21-61-A75, No. 14SF-61-A95,
and No. 6/5500/F-61-A43, all dated December 18, 1995, and Hamilton
Standard ASB's No. 14RF-9-61-A95, Revision 1, No. 14RF-19-61-A57,
Revision 1, No. 14RF-21-61-A75, Revision 1, No. 14SF-61-A95, Revision
1, and No. 6/5500/F-61-A43, Revision 1, all dated December 21, 1995,
was previously approved by the Director of the Federal Register as of
January 9, 1996 (61 FR 617).
The incorporation by reference of Hamilton Standard ASB's No. 14RF-
9-61-A94, Revision 1, dated March 6, 1996; No. 14RF-19-61-A53, Revision
1, dated March 6, 1996; No. 14RF-21-61-A72, Revision 1, dated March 6,
1996; No. 14SF-61-A92, Revision 1, dated March 6, 1996; and No. 6/5500/
F-61-A39, Revision 1, dated March 6, 1996; is approved by the Director
of the Federal Register as of May 9, 1996.
Comments for inclusion in the Rules Docket must be received on or
before June 24, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-ANE-05, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be
submitted to the following Internet address: ``epd-
[email protected]''.
[[Page 18053]]
The service information referenced in this AD may be obtained from
Hamilton Standard, One Hamilton Road, Windsor Locks, CT 06096-1010;
telephone (203) 654-6876. This information may be examined at the FAA,
New England Region, Office of the Assistant Chief Counsel, Burlington,
MA; or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
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) 238-7152, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: On December 26, 1995, the Federal Aviation
Administration (FAA) issued airworthiness directive (AD) 96-01-01,
Amendment 39-9477 (61 FR 617, January 9, 1996), applicable to Hamilton
Standard Models 14RF-9, -19, -21; and 14SF-5, -7, -11, -15, -17, -19,
and -23; and Hamilton Standard/British Aerospace 6/5500/F propellers,
to require all blades of applicable Hamilton Standard propellers be
calibrated for ultrasonic transmissibility before conducting the
ultrasonic shear wave inspection. In addition, that AD decreases the
repetitive inspection interval for the Hamilton Standard Models 14RF-9,
14SF-5, -7, -11, -15, -17, -19, and -23 propellers from 1,250 flight
cycles to 500 flight cycles. That AD also establishes a new ultrasonic
shear wave inspection interval of 1,000 flight cycles for the Hamilton
Standard Model 14RF-19, and 2,500 flight cycles for the Hamilton
Standard Model 14RF-21 and Hamilton Standard/British Aerospace Model 6/
5500/F. Also, that AD removes Hamilton Standard Model 14SFL11
propellers from service. That action was prompted by improvements in
the crack detection capability of the ultrasonic inspection method as
well as redefinition of crack growth rate. That condition, if not
corrected, could result in separation of a propeller blade due to
cracks initiating in the blade taper bore, that can result in aircraft
damage, and possible loss of aircraft control.
Since the issuance of that AD, the manufacturer has developed a new
taper bore repair process that consists of reaming damaged material out
of the taper bore, eddy current inspection (ECI) and fluorescent
penetrant inspection (FPI) of the taper bore, followed by a wall
thickness check and shotpeening. The FAA has evaluated the structural
adequacy of the repair action and has determined that design structural
integrity is maintained. In addition, the FAA has revised the cyclic
count determination procedure for Canadair CL215T and CL415 water
bomber aircraft. The FAA has determined that the water scoop mission
profile creates less stress than a touch-and-go or normal takeoff and
landing, and has therefore revised this AD to include the new cyclic
count definition of one-half flight cycle per each water scoop.
The FAA has reviewed and approved the technical contents of the
following Hamilton Standard Alert Service Bulletins (ASB's): No. 14RF-
9-61-A91, No. 14RF-19-61-A55, No. 14RF-21-61-A73, No. 14SF-61-A93, and
No. 6/5500/F-61-A41, all dated December 7, 1995, and No. 14RF-9-61-A91,
Revision 1, No. 14RF-19-61-A55, Revision 1, No. 14RF-21-61-A73,
Revision 1, No. 14SF-61-A93, Revision 1, all dated December 15, 1995,
and No. 6/5500/F-61-A41, Revision 1, dated December 18, 1995, that
describe procedures for ultrasonic shear wave inspections of the blade
taper bores for cracks after the lead wool has been removed. The
Revision 1 ASB's permit the installation of a plastic cone in the taper
bore that will enhance resistance to corrosion and mechanical damage.
Inspection procedures are the same.
In addition, the FAA has reviewed and approved the technical
contents of Hamilton Standard ASB's No. 14RF-9-61-A95, No. 14RF-19-61-
A57, No. 14RF-21-61-A75, No. 14SF-61-A95, and No. 6/5500/F-61-A43, all
dated December 18, 1995, and No. 14RF-9-61-A95, Revision 1, No. 14RF-
19-61-A57, Revision 1, No. 14RF-21-61-A75, Revision 1, No. 14SF-61-A95,
Revision 1, and No. 6/5500/F-61-A43, Revision 1, all dated December 21,
1995, that describe ultrasonic shear wave inspection that can be
accomplished without removing the lead from the taper bore which
permits an on-wing inspection of the blade taper bores for cracks. The
Revision 1 ASB's do not require immediate removal of the blades that
cannot be inspected for cracks due to the lead wool absorbing the
ultrasonic signal. These blades may be removed at any time within the
applicable compliance period. Inspection procedures are the same.
Also, the FAA has reviewed and approved technical contents of
Hamilton Standard ASB's No. 14RF-9-61-A94, Revision 1, dated March 6,
1996; No. 14RF-19-61-A53, Revision 1, dated March 6, 1996; No. 14RF-21-
61-A72, Revision 1, dated March 6, 1996; No. 14SF-61-A92, Revision 1,
dated March 6, 1996; and No. 6/5500/F-61-A39, Revision 1, dated March
6, 1996; that describe procedures for the new taper bore repair
process.
Since an unsafe condition has been identified that is likely to
exist or develop on other propellers of this same type design, this AD
supersedes AD 96-01-01 to require an ultrasonic shear wave inspection
of the propeller blade taper bore for cracks. Propeller blades with
ultrasonic shear wave readings that exceed the acceptable limits
described in the applicable ASB's must be removed from service and
replaced with serviceable propeller blades prior to further flight. In
addition, this AD requires the new taper bore repair for all Model
14RF-9 propellers no later than July 31, 1996, and for all other
affected propeller models February 28, 1997. Propeller blades that
cannot be repaired within the repair limits specified in the applicable
Hamilton Standard ASB's must be removed from service and replaced with
serviceable propeller blades prior to further flight. The calendar end-
date was determined based upon fracture mechanics and engineering
analysis, as well as logistics considerations, that support the
specified calendar end-date. This taper bore repair constitutes
terminating action to the repetitive ultrasonic taper bore inspections
required by this AD. The actions are required to be accomplished in
accordance with the service documents 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
[[Page 18054]]
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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 96-ANE-05.'' 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 removing Amendment 39-9477, (61 FR
617, January 9, 1996), and by adding a new airworthiness directive,
Amendment 39-9568, to read as follows:
96-08-02 Hamilton Standard: Amendment 39-9568. Docket 96-ANE-05.
Supersedes AD 96-01-01, Amendment 39-9477.
Applicability: Hamilton Standard Models 14RF-9, 14RF-19, 14RF-
21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19,
and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F
propellers installed on but not limited to Embraer EMB-120, EMB-
120RT; Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72, ATR72-
210; deHavilland DHC-8-100 series, DHC-8-200 series, DHC-8-300
series; SAAB-SCANIA SF 340B; Canadair CL-215T, CL-415;
Construcciones Aeronauticas SA (CASA) CN-235 series; and British
Aerospace ATP aircraft.
Note: 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 use
the authority provided in paragraph (u) to request approval from the
Federal Aviation Administration (FAA). This approval may address
either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe
condition described in this AD. Such a request should include an
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any propeller from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of a propeller blade due to cracks
initiating in the blade taper bore, that can result in aircraft
damage, and possible loss of aircraft control, accomplish the
following:
(a) For Hamilton Standard Model 14RF-9 propeller blades, with
Serial Numbers less than 882038 and listed in Hamilton Standard
Alert Service Bulletins (ASB's) No. 14RF-9-61-A95, dated December
18, 1995, or No. 14RF-9-61-A95, Revision 1, dated December 21, 1995,
installed on but not limited to Embraer EMB-120 and EMB-120RT series
aircraft, accomplish the following:
(1) Within the next 150 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14RF-9-61-A95, dated
December 18, 1995, or No. 14RF-9-61-A95, Revision 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 14RF-9-61-A91, dated
December 7, 1995, or No. 14RF-9-61-A91, Revision 1, dated December
15, 1995, perform an ultrasonic shear wave inspection in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95,
Revision 1, dated December 21, 1995, within 500 flight cycles since
last inspection or 150 flight cycles after the effective date of
this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14RF-9-61-A95, dated
December 18, 1995, or No. 14RF-9-61-A95, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995,
or No. 14RF-9-61-A91, Revision 1, dated December 15, 1995, within
the next 150 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95,
Revision 1, dated December 21, 1995, must be inspected in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-9-61-A91 dated December 7, 1995, or No. 14RF-9-61-A91, Revision
1 dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91,
Revision 1, dated December 15, 1995, must be removed from service
and replaced with a serviceable part prior to further flight.
(b) For Hamilton Standard Models 14SF-5, -7, -11, -15, and -23
propeller blades with Serial Numbers less than 882038 and listed in
Hamilton Standard ASB's No. 14SF-61-A95, dated December 18, 1995, or
No. 14SF-61-A95, Revision 1, dated December 21, 1995, installed on
but not limited to Aerospatiale ATR42-100, ATR42-300, ATR42-320,
ATR72 and deHavilland DHC-8-100, DHC-8-200, DHC-8-300 series
aircraft, accomplish the following:
(1) Within the next 150 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95, Revision 1, dated December
21, 1995.
[[Page 18055]]
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 14SF-61-A93, dated
December 7, 1995, or No. 14SF-61-A93, Revision 1, dated December 15,
1995, perform an ultrasonic shear wave inspection in accordance with
the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-
61-A95, dated December 18, 1995, or No. 14SF-61-A95, Revision 1,
dated December 21, 1995, within 500 flight cycles since last
inspection or 150 flight cycles after the effective date of this AD,
whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or
No. 14SF-61-A93, Revision 1, dated December 15, 1995, within the
next 150 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Revision
1, dated December 21, 1995, must be inspected in accordance with the
Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-
A93, dated December 7, 1995, or No. 14SF-61-A93, Revision 1, dated
December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Revision 1,
dated December 15, 1995, must be removed from service and replaced
with a serviceable part prior to further flight.
(c) For Hamilton Standard Model 14RF-9 propeller blades with
Serial Numbers less than 882038 and not listed in Hamilton Standard
ASB's No. 14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-
A95, Revision 1, dated December 21, 1995, installed on but not
limited to Embraer EMB 120 and EMB 120RT series aircraft, accomplish
the following:
(1) Within the next 300 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14RF-9-61-A95, dated
December 18, 1995, or No. 14RF-61-A95, Revision 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 14RF-9-61-A91, dated
December 7, 1995, or No. 14RF-9-61-A91, Revision 1, dated December
15, 1995, perform an ultrasonic shear wave inspection in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95,
Revision 1, dated December 21, 1995, within 500 flight cycles since
last inspection or 300 flight cycles after the effective date of
this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14RF-9-61-A95, dated
December 18, 1995, or No. 14RF-9-61-A95, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14RF-9-61-A91, dated December 7, 1995,
or No. 14RF-9-61-A91, Revision 1, dated December 15, 1995, within
the next 300 flight cycles after the effective date of this AD.-
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-9-61-A95, dated December 18, 1995, or No. 14RF-9-61-A95,
Revision 1, dated December 21, 1995, must be inspected in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91,
Revision 1, dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-9-61-A91, dated December 7, 1995, or No. 14RF-9-61-A91,
Revision 1, dated December 15, 1995, must be removed from service
and replaced with a serviceable part prior to further flight.
(d) For Hamilton Standard Models 14SF-5, -7, -11, -15, and -23
propeller blades with Serial Numbers less than 882038 and not listed
in ASB's No. 14SF-61-A95, dated December 18, 1995, or No. 14SF-61-
A95, Revision 1, dated December 21, 1995, installed on but not
limited to Aerospatiale ATR42-100, ATR42-300, ATR42-320, ATR72,
ATR72-210 and deHavilland DHC-8-100, DHC-8-200, DHC-8-300 series
aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95, Revision 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 14SF-61-A93, dated
December 7, 1995, or No. 14SF-61-A93, Revision 1, dated December 15,
1995, perform an ultrasonic shear wave inspection in accordance with
the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-
61-A95, dated December 18, 1995, or No. 14SF-61-A95, Revision 1,
dated December 21, 1995, within 500 flight cycles since last
inspection or 300 flight cycles after the effective date of this AD,
whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or
No. 14SF-61-A93, Revision 1, dated December 15, 1995, within the
next 300 flight cycles after the effective date of this AD. -
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Revision
1, dated December 21, 1995, must be inspected in accordance with the
Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-
A93, dated December 7, 1995, or No. 14SF-61-A93, Revision 1, dated
December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14SF-61-A93, dated December 7, 1995, or No. 14SF-61-A93, Revision 1,
dated December 15, 1995, must be removed from service and replaced
with a serviceable part prior to further flight.
(e) For all Hamilton Standard Models 14SF-17, and -19 propeller
blades with Serial Numbers less than 882038, installed on but not
limited to Canadair CL-215T and CL-415 series aircraft, accomplish
the following:
(1) Within the next 300 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95, Revision 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 14SF-61-A93, dated
December 7, 1995, or No. 14SF-61-A93, Revision 1, dated December 15,
1995, perform an ultrasonic shear wave inspection in accordance with
the Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-
61-A95, dated December 18, 1995, or No. 14SF-61-A95, Revision 1,
dated December 21, 1995, within 500 flight cycles since last
inspection or 300 flight cycles after the effective date of this AD,
whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or
No. 14SF-61-A93, Revision 1, dated December 15, 1995, within the
next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits
[[Page 18056]]
specified in Hamilton Standard ASB's No. 14SF-61-A95, dated December
18, 1995, or No. 14SF-61-A95, Revision 1, dated December 21, 1995,
must be removed from service and inspected in accordance with the
Accomplishment Instructions of Hamilton Standard ASB's No. 14SF-61-
A93, dated December 7, 1995, or No. 14SF-61-A93, Revision 1, dated
December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14SF-61-A93, dated December 7, 1995, or No. 14SF-61-93, Revision 1,
dated December 15, 1995, must be removed from service and replaced
with a serviceable part prior to further flight.
(f) For all Hamilton Standard Models 14RF-19 propeller blades
with Serial Numbers less than 882038, installed on but not limited
to SAAB-SCANIA SF 340B series aircraft, accomplish the following:
(1) Within the next 300 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14RF-19-61-A57, dated
December 18, 1995, or No. 14RF-19-61-A57, Revision 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 14RF-19-61-A55, dated
December 7, 1995, or No. 14RF-19-61-A55, Revision 1, dated December
15, 1995, perform an ultrasonic shear wave inspection in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-19-61-A57, dated December 18, 1995, or No. 14RF-19-61-A57,
Revision 1, dated December 21, 1995, within 1,000 flight cycles
since last inspection or 300 flight cycles after the effective date
of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14RF-19-61-A57, dated
December 18, 1995, or No. 14RF-19-61-A57, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14RF-19-61-A55, dated December 7, 1995,
or No. 14RF-19-61-A55, Revision 1, dated December 15, 1995, within
the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's 14RF-19-
61-A57, dated December 18, 1995, or No. 14RF-19-61-A57, Revision 1,
dated December 21, 1995, must be inspected in accordance with the
Accomplishment Instructions of Hamilton Standard ASB's No. 14RF-19-
61-A55, dated December 7, 1995, or No. 14RF-19-61-A55, Revision 1,
dated December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 1,000 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-19-61-A55, dated December 7, 1995, or No. 14RF-19-61-A55,
Revision 1, dated December 15, 1995, must be removed from service
and replaced with a serviceable part prior to further flight.
(g) For all Hamilton Standard Model 14RF-21 propeller blades
with Serial Numbers less than 882038, installed on but not limited
to Construcciones Aeronauticas SA (CASA) CN-235 series aircraft,
accomplish the following:
(1) Within the next 300 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 14RF-21-61-A75, dated
December 18, 1995, or No. 14RF-21-61-A75, Revision 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standard ASB's No. 14RF-21-61-A73, dated
December 7, 1995, or No. 14RF-21-61-A73, Revision 1, dated December
15, 1995, perform an ultrasonic shear wave inspection in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-21-61-A75, dated December 18, 1995, or No. 14RF-21-61-A75,
Revision 1, dated December 21, 1995, within 2,500 flight cycles
since last inspection or 300 flight cycles after the effective date
of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 14RF-21-61-A75, dated
December 18, 1995, or No. 14RF-21-61-A75, Revision 1, dated December
21, 1995, due to the lead wool absorbing the ultrasonic signal, must
be inspected in accordance with the Accomplishment Instructions of
Hamilton Standard ASB's No. 14RF-21-61-A73, dated December 7, 1995,
or No. 14RF-21-61-A73, Revision 1, dated December 15, 1995, within
the next 300 flight cycles after the effective date of this AD.
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-21-61-A75, dated December 18, 1995, or No. 14RF-21-61-A75,
Revision 1, dated December 21, 1995, must be inspected in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
14RF-21-61-A73, dated December 7, 1995, or No. 14RF-21-61-A73,
Revision 1, dated December 18, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 2,500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No.
14RF-21-61-A73, dated December 7, 1995, or No. 14RF-21-61-A73,
Revision 1, dated December 15, 1995, must be removed from service
and replaced with a serviceable part prior to further flight.
(h) For all Hamilton Standard/British Aerospace 6/5500/F
propeller blades, with Serial Numbers less than 882038, installed on
but not limited to British Aerospace ATP series aircraft, accomplish
the following:
(1) Within the next 300 flight cycles, after the effective date
of this AD, perform an ultrasonic shear wave inspection for cracks
in the blade taper bore in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 6/5500/F-61-A43, dated
December 18, 1995, or No. 6/5500/F-61-A43, Revision 1, dated
December 21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standards ASB's No. 6/5500/F-61-A41, dated
December 7, 1995, or No. 6/5500/F-61-A41, Revision 1, dated December
18, 1995, perform an ultrasonic shear wave inspection in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
6/5500/F-61-A43, dated December 18, 1995, or No. 6/5500/F-61-A43,
Revision 1, dated December 21, 1995, as applicable within 2,500
flight cycles since last inspection or 300 flight cycles after the
effective date of this AD, whichever occurs later.
(3) Propeller blades that cannot be inspected for cracks in
accordance with Hamilton Standard ASB's No. 6/5500/F-61-A43, dated
December 18, 1995, or No. 6/5500/F-61-A43, Revision 1, dated
December 21, 1995, due to the lead wool absorbing the ultrasonic
signal, must be inspected in accordance with the Accomplishment
Instructions of Hamilton Standard ASB's No. 6/5500/F-61-A41, dated
December 7, 1995, or No. 6/5500/F-61-A41, Revision 1, dated December
18, 1995, within the next 300 flight cycles after the effective date
of this AD.
(4) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No. 6/
5500/F-61-A43, dated December 18, 1995, or No. 6/5500/F-61-A43,
Revision 1, dated December 21, 1995, must be inspected in accordance
with the Accomplishment Instructions of Hamilton Standard ASB's No.
6/5500/F-61-A41, dated December 7, 1995, or No. 6/5500/F-61-A41
Revision 1, dated December 18, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 2,500 flight cycles in
accordance with the applicable ASB's.
(6) Propeller blades that have ultrasonic shear wave indications
that exceed the limits specified in Hamilton Standard ASB's No. 6/
5500/F-61-A41, dated December 7, 1995, or No. 6/5500/F-61-A41,
Revision 1, dated December 18, 1995, must be removed from service
and replaced with a serviceable part prior to further flight.
(i) For all Hamilton Standard Model 14SFL11 propellers installed
on Aerospatiale ATR72-210 series aircraft, remove these propellers
from service prior to further flight, and replace with serviceable
Hamilton Standard 247F propellers.
(j) The ultrasonic inspection of the propeller blade taper bore
must be performed by a Level II or III inspector who is qualified
under the guidelines established by the American Society of
Nondestructive Testing or MIL-STD-410 or FAA-approved equivalent,
and must be trained by Hamilton Standard-approved personnel on how
to do
[[Page 18057]]
this inspection procedure. The individual returning the aircraft to
service is required to verify that the ultrasonic inspection was
accomplished in accordance with the requirements of this paragraph.
(k) For repetitive inspections, propeller blades may be
evaluated to determine if the lead wool is absorbing the ultrasonic
signal at any time during the respective flight cycle repetitive
inspection interval to determine if the lead wool removal is
required to complete the ultrasonic shear wave inspection.
(l) No later than August 31, 1996, for all Model 14RF-9
propeller blades with S/N's less than 885718, perform the taper bore
repair, eddy current inspect (ECI) and fluorescent penetrant inspect
(FPI) the taper bore, perform a wall thickness check, and shotpeen,
in accordance with the procedures described in Hamilton Standard ASB
No. 14RF-9-61-A94, Revision 1, dated March 6, 1996. Propeller blades
repaired in accordance with the original issuance of Hamilton
Standard ASB No. 14RF-9-61-A94, dated February 6, 1996, need not be
repaired again. Propeller blades found to be beyond repair limits
specified in these ASB's must be removed from service.
(m) No later than February 28, 1997, for all Model 14RF-19
propeller blades with S/N's less than 885718, perform the taper bore
repair, ECI and FPI the taper bore, perform a wall thickness check,
and shotpeen, in accordance with the procedures described in
Hamilton Standard ASB No. 14RF-19-61-A53, Revision 1, dated March 6,
1996. Propeller blades repaired in accordance with the original
issuance of Hamilton Standard ASB No. 14RF-19-61-A53, dated February
6, 1996, need not be repaired again. Propeller blades found to be
beyond repair limits specified in these ASB's must be removed from
service.
(n) No later than February 28, 1997, for all Model 14RF-21
propeller blades with S/N's less than 885718, perform the taper bore
repair, ECI and FPI the taper bore, perform a wall thickness check,
and shotpeen, in accordance with the procedures described in
Hamilton Standard ASB No. 14RF-21-61-A72, Revision 1, dated March 6,
1996. Propeller blades repaired in accordance with the original
issuance of Hamilton Standard ASB No. 14RF-21-61-A72, dated February
6, 1996, need not be repaired again. Propeller blades found to be
beyond repair limits specified in these ASB's must be removed from
service.
(o) No later than February 28, 1997, for all Model 14SF
propeller blades with S/N's less than 885718, perform the taper bore
repair, ECI and FPI the taper bore, perform a wall thickness check,
and shotpeen, in accordance with the procedures described in
Hamilton Standard ASB No. 14SF-61-A92, Revision 1, dated March 6,
1996. Propeller blades repaired in accordance with the original
issuance of Hamilton Standard ASB No. 14SF-61-A92, dated February 6,
1996, need not be repaired again. Propeller blades found to be
beyond repair limits specified in these ASB's must be removed from
service.
(p) No later than February 28, 1997, for all Model 6/5500/F
propeller blades with S/N's less than 885718, perform the taper bore
repair, ECI and FPI the taper bore, perform a wall thickness check,
and shotpeen, in accordance with the procedures described in
Hamilton Standard ASB No. 6/5500/F-61-A39, Revision 1, dated March
6, 1996. Propeller blades repaired in accordance with the original
issuance of Hamilton Standard ASB No. 6/5500/F-61-A39, dated
February 6, 1996, need not be repaired again. Propeller blades found
to be beyond repair limits specified in these ASB's must be removed
from service.
(q) Performing the requirements of paragraphs (l), (m), (n),
(o), or (p) of this AD, as applicable, constitutes terminating
action to the repetitive ultrasonic shear wave inspection
requirements of this AD.
(r) For the purpose of this AD, a flight cycle is defined as one
takeoff and the next landing of an aircraft. In addition, each touch
and go is defined as a flight cycle.
(s) For propellers installed on Canadair CL-215T and CL-415
water bomber aircraft, each water scoop constitutes one-half flight
cycle.
(t) Propeller blades removed from service after inspections
performed in accordance with AD 95-18-06 R1 or 96-01-01, and
subsequently repaired in accordance with the requirements of this AD
and found to be serviceable, may be returned to service.
(u) 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.
(v) 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 aircraft to a location where
the requirements of this AD can be accomplished.
(w) The actions required by this AD shall be done in accordance
with the following service documents:
----------------------------------------------------------------------------------------------------------------
Document No.- Pages- Revision- Date
----------------------------------------------------------------------------------------------------------------
No. 14RF-9-61-A91--.................. 1-40- Original-.................... Dec. 7, 1995.
Total Pages: 40
No. 14RF-9-61-A91--.................. 1-42- 1--.......................... Dec. 15, 1995.
Total Pages: 42
No. 14RF-19-61-A55--................. 1-40- Original-.................... Dec. 7, 1995.
Total Pages: 40
No. 14RF-19-61-A55--................. 1-42- 1--.......................... Dec. 15, 1995.
Total Pages: 42
No. 14RF-21-61-A73--................. 1-40- Original-.................... Dec. 7, 1995.
Total Pages: 40
No. 14RF-21-61-A73--................. 1-42- 1--.......................... Dec. 15, 1995.
Total Pages: 42
No. 14SF-61-A93-..................... 1-40- Original-.................... Dec. 7, 1995.
Total Pages: 40
No. 14SF-61-A93-..................... 1-42- 1--.......................... Dec. 15, 1995.
Total Pages: 42
No. 6/5500/F-61-A41---............... 1-40- Original-.................... Dec. 7, 1995.
Total Pages: 40
No. 6/5500/F-61-A41---............... 1-42- 1--.......................... Dec. 18, 1995.
Total Pages: 42
No. 14RF-9-61-A95---................. 1-36- Original-.................... Dec. 18, 1995.
Total Pages: 36
No. 14RF-9-61-A95---................. 1-36- 1--.......................... Dec. 21, 1995.
Total Pages: 36
No. 14RF-19-61-A57---................ 1-35- Original-.................... Dec. 18, 1995.
Total Pages: 35
No. 14RF-19-61-A57---................ 1-35- 1--.......................... Dec. 21, 1995.
Total Pages: 35
No. 14RF-21-61-A75---................ 1-35- Original-.................... Dec. 18, 1995.
[[Page 18058]]
Total Pages: 35
No. 14RF-21-61-A75---................ 1-35- 1--.......................... Dec. 21, 1995.
Total Pages: 35
No. 14SF-61-A95-..................... 1-37- Original-.................... Dec. 18, 1995.
Total Pages: 37
No. 14SF-61-A95-..................... 1-37- 1--.......................... Dec. 21, 1995.
Total Pages: 37
No. 6/5500/F-61-A43---............... 1-35- Original-.................... Dec. 18, 1995.
Total Pages: 35
No. 6/5500/F-61-A43---............... 1-35- 1--.......................... Dec. 21, 1995.
Total Pages: 35
No. 14RF-9-61-A94---................. 1-80- 1--.......................... Mar. 6, 1996.
Total Pages: 80
No. 14RF-19-61-A53---................ 1-77- 1--.......................... Mar. 6, 1996.
Total Pages: 77
No. 14RF-21-61-A72---................ 1-77- 1--.......................... Mar. 6, 1996.
Total Pages: 77
No. 14SF-61-A92---................... 1-79- 1--.......................... Mar. 6, 1996.
Total Pages: 79
No. 6/5500/F-61-A39---............... 1-77- 1--.......................... Mar. 6, 1996.
Total Pages: 77
----------------------------------------------------------------------------------------------------------------
The incorporation by reference of Hamilton Standard Alert
Service Bulletins (ASB's): No. 14RF-9-61-A91, No. 14RF-19-61-A55,
No. 14RF-21-61-A73, No. 14SF-61-A93, and No. 6/5500/F-61-A41, all
dated December 7, 1995, and Hamilton Standard ASB's No. 14RF-9-61-
A91, Revision 1, No. 14RF-19-61-A55, Revision 1, No. 14RF-21-61-A73,
and Revision 1, No. 14SF-61-A93, all dated December 15, 1995, and
No. 6/5500/F-61-A41, Revision 1, dated December 18, 1995; and
Hamilton Standard ASB's No. 14RF-9-61-A95, No. 14RF-19-61-A57, No.
14RF-21-61-A75, No. 14SF-61-A95, and No. 6/5500/F-61-A43, all dated
December 18, 1995, and Hamilton Standard ASB's No. 14RF-9-61-A95,
Revision 1, No. 14RF-19-61-A57, Revision 1, No. 14RF-21-61-A75,
Revision 1, No. 14SF- 61-A95, Revision 1, and No. 6/5500/F-61-A43,
Revision 1, all dated December 21, 1995, was previously approved by
the Director of the Federal Register as of January 9, 1996, (61 FR
617). For those documents not previously approved for incorporation
by reference, the 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 for those documents not previously approved.
Copies may be obtained from Hamilton Standard, One Hamilton Road,
Windsor Locks, CT 06096-1010; telephone (203) 654-6876. Copies may
be inspected at the FAA, New England Region, Office of the Assistant
Chief 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.
(x) This amendment becomes effective on May 9, 1996.
Issued in Burlington, Massachusetts, on April 16, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 96-9806 Filed 4-23-96; 8:45 am]
BILLING CODE 4910-13-U