[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]



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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.

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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