[Federal Register Volume 61, Number 150 (Friday, August 2, 1996)]
[Rules and Regulations]
[Pages 40313-40315]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-19560]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-ANE-04; Amendment 39-9705, AD 96-08-01 R1]


Airworthiness Directives; Hamilton Standard Model 14RF-9 
Propellers

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment revises airworthiness directive (AD) 96-08-01, 
that is applicable to Hamilton Standard Model 14RF-9 propellers. The 
current AD superseded priority letter AD 95-24-09, and requires an 
ultrasonic shear wave inspection, adds a one-time visual and 
fluorescent penetrant inspection, and repair of the propeller blade 
shank. This revision will add a new shank eddy current inspection and 
will allow repair of certain blade shanks removed from service under 
the current AD. The actions specified by this AD are intended to 
prevent propeller blade separation due to propeller blade shank 
cracking that can result in loss of control of the aircraft.

DATES: Effective August 2, 1996.
    The incorporation by reference of Hamilton Standard Service 
Bulletins (SB) Nos. 14RF-9-61-86, Revision 4, dated November 9, 1995, 
Alert Service Bulletin No. 14RF-9-61-A90, Original, dated November 9, 
1995, and Alert Service Bulletin No. 14RF-9-61-A92, Revision 2, dated 
March 6, 1996, and listed in the regulations was approved by the 
Director of the Federal Register as of May 1, 1996 (61 FR 16618, 4/16/
96). The incorporation by reference of Hamilton Standard Service 
Bulletin No. 14RF-9-61-105, Original, dated July 24, 1996, is approved 
by the Director of the Federal Register as of August 2, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before September 16, 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-04, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be 
submitted to the Rules Docket by using the following Internet 
address:``[email protected]''. All comments must contain 
the Docket No. in the subject line of the comment. Comments may be 
inspected at this location between 8:00 a.m. and 4:30 p.m.
    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 and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (617) 238-7158, fax (617) 238-7199.

SUPPLEMENTARY INFORMATION: On April 1, 1996, the Federal Aviation 
Administration (FAA) issued airworthiness directive (AD) 96-08-01, 
applicable to Hamilton Standard Model 14RF-9 propellers, which 
superseded priority letter AD 95-24-09, and requires an ultrasonic 
shear wave inspection for cracks or surface indications, a one-time 
visual and flourescent penetrant inspection for mechanical damage, and 
repair of the propeller blade shank. That action was prompted by a 
report of an inflight loss of a Hamilton Standard Model 14RF-9 
propeller blade installed on an Embraer EMB-120 aircraft. The loss of 
the propeller blade resulted in the subsequent loss of the propeller 
and portions of the gearbox. The propeller blade separated due to a 
crack approximately 9 inches from the butt end of the blade. The FAA 
determined that the crack initiated on the outer

[[Page 40314]]

surface of the blade shank in an area of mechanical damage induced as a 
result of a localized interference condition between the blade spar and 
the foam mold which occurred during blade manufacture. That condition, 
if not corrected, could result in propeller blade separation due to 
propeller blade shank cracking, which could result in loss of control 
of the aircraft.
    Since the issuance of that AD, the manufacturer has developed new 
inspection and repair procedures for mechanical damage (dents) greater 
than .005 inches deep to a maximum of .010 inches in depth. The new 
inspection and repair procedures will ensure that the structural 
integrity of the blades is maintained. Also, the new inspection and 
repair procedures will allow certain blades having dents greater than 
.005 inches deep that were removed from service in accordance with AD 
96-08-01 to be inspected and repaired in accordance with Hamilton 
Standard Service Bulletin No. 14RF-9-61-105, dated July 24, 1996, and 
returned to service.
    The new inspection procedure can find damage in areas of the 
propeller blade shank that might have been damaged by interference with 
the propeller blade foam mold during manufacture. The damage will be 
visible when the overlying fiberglass and adhesive layers are removed. 
Prior to returning damaged propeller blades to service, blades must be 
repaired in accordance with the applicable service or alert service 
bulletin.
    The FAA has reviewed and approved the technical contents of 
Hamilton Standard Service Bulletin (SB) No. 14RF-9-61-86, Revision 4, 
and Alert Service Bulletin (ASB) No. 14RF-9-61-A90, both dated November 
9, 1995, that describe procedures for an ultrasonic shear wave 
inspection of propeller blade shanks for cracks or surface indications; 
and Hamilton Standard ASB No. 14RF-9-61-A92, Revision 2, dated March 6, 
1996, that describes procedures for an inspection and repair for 
mechanical damage. In addition, the FAA has reviewed and approved the 
technical contents of Hamilton Standard SB No. 14RF-9-61-105, Original, 
dated July 24, 1996, which describes eddy current inspection and repair 
procedures for those propeller blades with dents that exceed .005 
inches deep to a maximum of .010 inches in depth.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other propellers of this same type design, this AD 
revises AD 96-08-01, by adding a new paragraph (d) which allows 
inspection and repair of propeller blades with mechanical damage 
greater than .005 inches deep to a maximum of .010 inches in depth in 
accordance with Hamilton Standard Service Bulletin No. 14RF-9-61-105, 
dated July 24, 1996. This revision will also enable those propellers 
that were removed from service in accordance with AD 96-08-01, and that 
are determined repairable in accordance with SB 14RF-9-61-105, to be 
returned to service.
    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 96-ANE-04.'' 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 revised to read as follows:

96-08-01R1  Hamilton Standard: Amendment 39-9707. Docket No. 96-ANE-
04, revises AD 96-08-01, Amendment No. 39-9567.

    Applicability: Hamilton Standard Model 14RF-9 propellers, 
installed on but not limited to Embraer EMB-120 series 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 (e) to request approval from the 
Federal Aviation Administration (FAA). This approval may

[[Page 40315]]

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 propeller blade separation due to propeller blade 
shank cracking, which could result in loss of control of the 
aircraft, accomplish the following:
    (a) Propeller blades that have been ultrasonically shear wave 
inspected in accordance with the requirements of AD 95-24-09 or AD 
96-08-01 need not undergo another ultrasonic shear wave inspection 
in accordance with paragraph (b) of this AD. All affected propeller 
blades with S/N's less than 885751, however, must be inspected for 
mechanical damage in accordance with paragraph (c) of this AD by 
August 31, 1996. Propeller blades with S/N's less than 885751 that 
have not been ultrasonically shear wave inspected in accordance with 
AD 95-24-09 or AD 96-08-01 must undergo ultrasonic shear wave 
inspection in accordance with paragraph (b) of this AD prior to 
further flight, and must be inspected for mechanical damage in 
accordance with paragraph (c) of this AD by August 31, 1996; or must 
be inspected for mechanical damage in accordance with paragraph (c) 
of this AD prior to further flight.
    (b) Prior to further flight, perform an ultrasonic shear wave 
inspection for cracks or surface indications in accordance with the 
applicable Hamilton Standard Service Bulletin (SB) or Alert Service 
Bulletin (ASB) described in paragraphs (b)(1) and (b)(2) of this AD 
unless accomplished previously in accordance with AD 95-24-09 or AD 
96-08-01. Prior to further flight, remove from service propeller 
blades with ultrasonic shear wave readings that exceed the 
acceptable limits described in the applicable SB or ASB, and replace 
with serviceable propeller blades:
    (1) Inspect, and if necessary, remove and replace with a 
serviceable propeller blade, in accordance with the Accomplishment 
Instructions of Hamilton Standard SB No. 14RF-9-61-86, Revision 4, 
dated November 9, 1995, propeller blade shanks with propeller blade 
spars, Part Number (P/N) 792231-1. These propeller blades may be 
identified by, but not limited to, Serial Numbers (S/N's) 853445 and 
higher except for the S/N's listed in Table 1 of this SB. Propeller 
blades inspected in accordance with the Original, Revision 1, 
Revision 2, or Revision 3 of Hamilton Standard SB No. 14RF-9-61-86, 
and which passed inspection, need not be ultrasonically shear wave 
inspected again.
    (2) Remove propeller blade for off-wing inspection, inspect, and 
if necessary, replace with a serviceable propeller blade, in 
accordance with the Accomplishment Instructions of Hamilton Standard 
ASB No. 14RF-9-61-A90, dated November 9, 1995, propeller blade 
shanks with propeller blade spars, P/N 782683-1. These propeller 
blades may be identified by, but not limited to, S/N's less than 
853445, and propeller blades with S/N's greater than 853445 that are 
listed in Table 1 of this ASB.
    (c) Perform a one-time visual and fluorescent penetrant 
inspection of the propeller blade shank for mechanical damage by 
August 31, 1996, in accordance with the Accomplishment Instructions 
of Hamilton Standard ASB No. 14RF-9-61-A92, Revision 2, dated March 
6, 1996, on all propeller blade shanks with S/N's before 885751. 
Propeller blades inspected in accordance with the original or 
Revision 1 of Hamilton Standard ASB No. 14RF-9-61-A92, and which 
passed inspection or were repaired, need not be inspected again.
    (1) Prior to further flight, remove from service propeller 
blades with mechanical damage that exceed repair limits specified in 
ASB No. 14RF-9-61-A92, Revision 2, dated March 6, 1996, and replace 
with serviceable parts.
    (2) Prior to further flight, repair propeller blades with 
repairable damage in accordance with the procedures described in ASB 
No. 14RF-9-61-A92, Revision 2, dated March 6, 1996.
    (d) Propeller blades removed from service in accordance with 
paragraph (c) of this AD, may be returned to service provided the 
blades are inspected for cracks and repaired in accordance with the 
procedures described in Hamilton Standard SB No. 14RF-9-61-105, 
dated July 24, 1996. Blades with damage that exceed repair limits 
specified in Hamilton Standard SB 14RF-9-61-105, dated July 24, 
1996, cannot be returned to service.
    (e) 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.

    (f) 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.
    (g) The actions required by this AD shall be performed in 
accordance with Hamilton Standard Service Bulletin (SB) No. 14RF-9-
61-86, Pages 1-34, Revision 4, dated November 9, 1995, Hamilton 
Standard Alert SB No. 14RF-9-61-A90, Pages 1- 39, Original, dated 
November 9, 1995; Hamilton Standard Alert SB No. 14RF-9-61-A92, 
Pages 1-44, Revision 2, dated March 6, 1996, and Hamilton Standard 
SB No. 14RF-9-61-105, Pages 1-23, Original, dated July 24, 1996. The 
incorporation of Hamilton Standard ASB Nos. 14RF-9-61- 86, 14RF-9-
61-A90, and 14RF-9-61-A92, was approved previously in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51 as of May 1, 1996 (61 FR 
16618, 4/16/96). The incorporation by reference of Hamilton Standard 
Service Bulletin No. 14RF-9-61-105, Pages 1-23, Original dated July 
24, 1996, was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of August 2, 
1996. 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.
    (h) This amendment revises AD 96-08-01, issued April 1, 1996.
    (i) This amendment becomes effective on August 2, 1996.

    Issued in Burlington, Massachusetts, on July 27, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 96-19560 Filed 7-31-96; 10:38 am]
BILLING CODE 4910-13-U