[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