[Federal Register Volume 61, Number 6 (Tuesday, January 9, 1996)]
[Rules and Regulations]
[Pages 617-622]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-268]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-ANE-73; Amendment 39-9477, AD 96-01-01]
Airworthiness Directives; Hamilton Standard Propellers 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
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 Hamilton Standard Propeller 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. This
action supersedes priority letter AD 95-18-06R1, that was issued on
August 30, 1995, that currently requires ultrasonic shear wave
inspection on all Hamilton Standard 14RF-9 propeller blades, and
ultrasonic shear wave inspection on certain Hamilton Standard Propeller
Models 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 propeller blades. This action requires that all blades of
applicable Hamilton Standard propellers be calibrated for ultrasonic
transmissibility before conducting the ultrasonic shear wave
inspection. This action improves the crack detection capability of the
ultrasonic shear wave inspection. This action also decreases the
repetitive inspection interval for the 14RF-9, 14SF-5, -7, -11, -15, -
17, -19, and -23 from 1,250 flight cycles to 500 flight cycles. This
action also establishes a new ultrasonic shear wave inspection interval
of 1,000 flight cycles for the 14RF-19 and 2,500 flight cycles for the
14RF-21 and the 6/5500/F. This AD also removes 14SFL11 propellers from
service. This AD is prompted by reports that the existing ultrasonic
shear wave inspection may not detect cracks as originally determined
with some blades due to geometric differences. 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 the aircraft.
DATES: Effective January 19, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 19, 1996.
Comments for inclusion in the Rules Docket must be received on or
before January 29, 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. 95-ANE-73, 12 New England
Executive Park, Burlington, MA 01803-5299.
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, 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: Frank Walsh, Aerospace Engineer,
Boston Aircraft Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803,
telephone (617) 238-7152, fax: (617) 238-7199.
SUPPLEMENTARY INFORMATION: On August 30, 1995, the Federal Aviation
Administration (FAA) issued priority letter airworthiness directive
(AD) 95-18-06R1 applicable to Hamilton Standard Propeller 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, which requires ultrasonic shear wave inspection on
all Hamilton Standard 14RF-9 propeller blades, and ultrasonic shear
wave inspection on certain Hamilton Standard Models 14RF-19, -21; and
14SF-5, -7, -11, L11, -15, -17, -19, and -23; and Hamilton Standard/
British Aerospace 6/5500/F propeller blades. That AD action was
prompted by a report of a Hamilton Standard 14RF-9 propeller blade
installed on an Embraer EMB-120 aircraft that had separated inflight.
Since the issuance of that priority letter AD, the FAA and Hamilton
Standard have been working to improve the crack detection capability of
the ultrasonic inspection method as well as working to refine the crack
growth rate prediction methodology. The results of this work form the
basis for the new inspection method and the change in repetitive
inspection interval. This AD will require that propeller blades be
calibrated for ultrasonic transmissibility before conducting an
ultrasonic shear wave inspection, thereby improving the detection
capability of the ultrasonic shear wave inspection technique. This
action will also decrease the repetitive inspection interval for the
14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 from 1,250 flight
cycles to 500 flight cycles. This action will further establish a new
ultrasonic shear wave inspection interval of 1,000 flight cycles for
the 14RF-19 and 2,500 flight cycles for the 14RF-21 and the 6/5500/F
propeller models. This AD also requires removal of the life limited
14SFL11 propellers currently in service, approximately four propellers.
These 14SFL11 propellers will be replaced with the Hamilton Standard
Model 247F propellers. The actions specified by this AD are intended to
prevent the 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.
This AD references two ultrasonic inspection methods, one that can
be accomplished without removing the lead from the taper bore which
permits an on wing inspection and a second inspection that requires the
blade be removed and inspected at an FAA approved facility. The
inspection that is conducted without removing the lead from the taper
bore cannot be accomplished on some blades because of ultrasonic
transmissibility problems caused by the lead wool absorbing the signal.
These blades must be removed and inspected at an FAA approved facility
where the lead wool will be extracted.
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,
Rev 1, No. 14RF-19-61-A55, Rev 1, No. 14RF-21-61-A73, Rev 1, No. 14SF-
61-A93, Rev 1, and No. 6/5500/F-61-A41, Rev 1, all dated December 15,
1995, that describe procedures for ultrasonic shear wave inspections of
the blade taper bores for cracks after the lead wool has
[[Page 618]]
been removed. The Rev. 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 approved 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, Rev 1, No.
14RF-19-61-A57, Rev 1, No. 14RF-21-61-A75, Rev 1, No. 14SF-61-A95, Rev
1, and No. 6/5500/F-61-A43, Rev 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 Rev. 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.
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 priority letter AD 95-18-06R1 to require all Hamilton
Standard Model 14RF-9, -19, -21; and 14SF-5, -7, -11, -15, -17, -19,
and -23; and Hamilton Standard/British Aerospace 6/5500/F propeller
blades be calibrated for ultrasonic transmissibility before conducting
an ultrasonic shear wave inspection. The actions and inspection
intervals for each propeller model are required to be accomplished in
accordance with the service bulletins 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 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 95-ANE-73.'' 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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-01-01 Hamilton Standard: Amendment 39-9477. Docket No. 95-ANE-73.
Supersedes AD 95-18-06R1.
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 (n) 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, Rev 1, dated December 21, 1995,
installed on but not limited to Embraer EMB-120 and EMB-120RT series
aircraft, accomplish the following:
[[Page 619]]
(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, Rev 1, dated December 21,
1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standard ASB's No. 14RF-9-61-A91, dated
December 7, 1995, or No. 14RF-9-61-A91, Rev 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, Rev 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, Rev 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, Rev 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, Rev 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, Rev 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 SB'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, Rev 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, Rev 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, Rev 1, dated December 21,
1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standard ASB's No. 14SF-61-A93, dated
December 7, 1995, or No. 14SF-61-A93, Rev 1, dated December 15,
1995, perform an ultrasonic shear wave inspection in accordance with
the Accomplishments Instructions of Hamilton Standard ASB's No.
14SF-61-A95, dated December 18, 1995, or No. 14SF-61-A95, Rev 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, Rev 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, Rev 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, 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, Rev 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 SB'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, Rev 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, Rev 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, Rev 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, Rev 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, Rev 1,
dated December 21, 1995, within 300 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, Rev. 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, Rev. 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, 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 Rev. 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 SB'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, Rev. 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, -17, -19,
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, Rev. 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 Rev. 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, Rev. 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, Rev. 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-
[[Page 620]]
A95, Rev. 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, Rev. 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, Rev. 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, Rev. 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 SB'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, Rev. 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, Rev. 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, Rev. 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, Rev. 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, Rev. 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, Rev. 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 Rev. 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 Rev. 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 SB'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, Rev. 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, Rev. 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, Rev. 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 Rev. 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. 14SF-61-A95, dated
December 18, 1995, or No. 14SF-61-A95 Rev. 1, dated December 21,
1995, due to the lead wool absorbing the ultrasonic signal inspect
in accordance with the Accomplishment Instructions of Hamilton
Standard ASB's No. 14SF-61-A93, dated December 7, 1995, or No. 14SF-
61-A93, Rev. 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, Rev. 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, Rev. 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 SB'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, Rev.
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 Aeronautic 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-61-A75, Rev. 1, dated December 21,
1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standard ASB's No. 14RF-19-61-A55, dated
December 7, 1995, or No. 14RF-19-61-A55, Rev. 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, Rev. 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-21-61-A75, dated
December 18, 1995, or No. 14RF-61-A75, Rev. 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, Rev. 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, Rev.
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, Rev. 1, dated
December 15, 1995.
(5) Thereafter, perform repetitive ultrasonic shear wave
inspections at intervals not to exceed 2,500 flight cycles in
accordance with the applicable SB'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, Rev.
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
[[Page 621]]
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, Rev. 1, dated December
21, 1995.
(2) For propeller blades that have been previously inspected in
accordance with Hamilton Standard ASB's No. 6/5500/F-61-A41, dated
December 7, 1995, or No. 6/5500/F-61-A41, Rev. 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, or No. 6/5500/F-61-A43, Rev. 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, Rev. 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, Rev. 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, Rev.
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, Rev. 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 SB'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, Rev.
1, dated December 18, 1995, must be removed from service and
replaced with a serviceable part prior to further flight.
(i) For all currently installed Hamilton Standard Model 14SFL11
propellers installed on Aerospatiale ATR72-210 series aircraft
remove all 14SFL11 propellers from service within the next 150
flight cycles, after the effective date of this AD, 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 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 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 500 flight cycle repetitive inspection
interval to determine if the lead wool removal is required to
complete the ultrasonic shear wave inspection.
(l) 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, and each water load pickup for
amphibian aircraft operation is defined as a flight cycle.
(m) Propeller blades removed from service after inspections
performed in accordance with AD 95-18-06R1, and subsequently
inspected in accordance with the requirements of this AD and found
to be serviceable, may be returned to service.
(n) 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.
(o) 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.
(p) The ultrasonic shear wave inspections and removal and
replacement of propeller blades shall be done in accordance with the
following Hamilton Standard Alert Service Bulletins:
------------------------------------------------------------------------
Document No. Revision Date
------------------------------------------------------------------------
No. 14RF-9-61-A91; Total Pages:40. ........ Dec. 7, 1995.
No. 14RF-9-61-A91; Total Pages: 42 1 Dec. 15, 1995.
No. 14RF-19-61-A55; Total Pages: ........ Dec. 7, 1995.
40.
No. 14RF-19-61-A55; Total Pages: 1 Dec. 15, 1995.
42.
No. 14RF-21-61-A73; Total Pages: ........ Dec. 7, 1995.
40.
No. 14RF-21-61-A73; Total Pages: 1 Dec. 15, 1995.
42.
No. 14SF-61-A93; Total Pages: 40.. ........ Dec. 7, 1995.
No. 14SF-61-A93, Total Pages: 42.. 1 Dec. 15, 1995.
No. 6/5500/F-61-A41; Total Pages: ........ Dec. 7, 1995.
40.
No. 6/5500/F-61-A41; Total Pages: 1 Dec. 18, 1995.
42.
No. 14RF-9-61-A95; Total Pages: 36 ........ Dec. 18, 1995.
No. 14RF-9-61-A95; Total Pages: 36 1 Dec. 21, 1995.
No. 14RF-19-61-A57; Total Pages: ........ Dec. 18, 1995.
35.
No. 14RF-19-61-A57; Total Pages: 1 Dec. 21,1995.
35.
No. 14RF-21-61-A75, Total Pages: ........ Dec. 18, 1995.
35.
No. 14RF-21-61-A75; Total Pages: 1 Dec. 21,1995.
35.
No. 14SF-61-A95; Total Pages: 37.. ........ Dec. 18, 1995.
No. 14SF-61-A95; Total Pages: 37.. 1 Dec. 21, 1995.
No. 6/5500/F-61-A43; Total Pages: ........ Dec. 18, 1995.
35.
No. 6/5500/F-61-A43; Total Pages: 1 Dec. 21, 1995.
35.
------------------------------------------------------------------------
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 Hamilton Standard, One Hamilton
Road, Windsor Locks, CT 06096-1010; telephone (203) 654-6876. This
information 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.
(q) This amendment supersedes priority letter AD 95-18-06R1,
issued August 30, 1995.
(r) This amendment becomes effective on January 19, 1996.
[[Page 622]]
Issued in Burlington, Massachusetts, on December 26, 1995.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 96-268 Filed 1-8-96; 8:45 am]
BILLING CODE 4910-13-U