[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current AD superseded priority letter AD 95-24-09, and requires an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]
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