[Federal Register Volume 62, Number 166 (Wednesday, August 27, 1997)]
[Rules and Regulations]
[Pages 45309-45313]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-22677]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-ANE-40; Amendment 39-10112; AD 97-18-02]
RIN 2120-AA64
Airworthiness Directives; Hartzell Propeller Inc. ( )HC-(
)(2,3)(X,V)( )-( ) Series and HA-A2V20-1B Series Propellers With
Aluminum Blades
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes four existing airworthiness
directives (ADs), applicable to Hartzell Propeller Inc. ( )HC-(
)(2,3)(X,V)( )-( ) series propellers with aluminum blades, that
currently require inspections for cracks in blade shanks and clamps.
This amendment requires initial and repetitive dye penetrant and eddy
current inspections of the blade and an optical comparator inspection
of the blade retention area, and, if necessary, replacement with
serviceable parts. In addition, this AD requires initial and repetitive
visual and magnetic particle inspection of the blade clamp, dye
penetrant inspection of the blade internal bearing bore, and, if
necessary, replacement with serviceable parts. Also, for all HC-
(1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, this AD requires an
additional initial and repetitive visual and magnetic particle
inspection of the hub and, if necessary, replacement with serviceable
parts. This amendment is prompted by reports of cracked blades, blade
clamps, and hubs and reports of blade separations. The actions
specified by this AD are intended to prevent blade separation due to
cracked blades, hubs, or blade clamps, which can result in loss of
control of the airplane.
DATES: Effective September 11, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 11, 1997.
Comments for inclusion in the Rules Docket must be received on or
before October 27, 1997.
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-40, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. Comments sent via the Internet must contain
the docket number in the subject line.
The service information referenced in this AD may be obtained from
Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634,
ATTN: Product Support; telephone (937) 778-4200, fax (937) 778-4321.
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: Tomaso DiPaolo, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate,
2300 East Devon Ave., Des Plaines, IL 60018; telephone (847) 294-7031,
fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
issued airworthiness directive (AD) 68-13-02, Amendment 39-614 (33 FR
9252, June 22, 1968), applicable to Hartzell Propeller Inc. Model PHC-
A3VF-4/V8433-2R and -4R propellers, to require repetitive inspections
for cracks in blade shanks at intervals not to exceed 400 hours Time in
Service (TIS). That action was prompted by reports of cracks in blade
shanks. That condition, if not corrected, could result in loss of a
blade due to blade shank cracks, which could result in loss of aircraft
control.
The FAA issued AD 68-19-04, Amendment 39-868 (34 FR 18296, November
15, 1969), applicable to Hartzell Propeller Inc. Model HC-A2XF, HC-
12X20, HC-82VF, BHC-A2XF, HC-13X20, HC-82VK, HC-A2XK, HC-D3X20, HC-
82VL, HC-A2XL, HC-82X20, HC-83XF, HC-A3XK, HC-82XF, HC-83XK, HC-A3VK,
HC-82XG, HC-83X20, HC-82XK, and HC-82KL propellers, with 8433, V8433,
8833, and V8833 blades, to require repetitive inspections for cracks in
blade shanks at intervals not to exceed 1,000 hours TIS. That action
was prompted by reports of cracks in blade shanks. That condition, if
not corrected, could result in loss of a blade due to blade shank
cracks,
[[Page 45310]]
which could result in loss of aircraft control.
The FAA issued AD 75-17-34, Amendment 39-2337 (40 FR 33433, August
8, 1975), applicable to Hartzell Propeller Inc. Model EHC-A3VF-2B/
V7636D propellers installed on Teledyne Continental Motors Model IO-
520-E series engines and on the deHavilland Heron D.H. 114 Series
aircraft in accordance with STC SA1685WE, to require repetitive
inspections for cracks in blade shanks and clamps at intervals not to
exceed 1,000 hours TIS. That action was prompted by reports of cracks
in blade shanks and clamps. That condition, if not corrected, could
result in loss of a blade due to blade shank and clamp cracks, which
could result in loss of aircraft control.
The FAA issued AD 77-14-07, Amendment 39-2955 (42 FR 35638, July
11, 1977), applicable to Hartzell Propeller Inc. Model EHC-A3VF-2B/
V7636N propellers installed on Teledyne Continental Motors Model IO-
520-E series engines and on the deHavilland Heron D.H. 114 Series
aircraft in accordance with STC SA1685WE, to require repetitive
inspections for cracks in certain blade clamps at intervals not to
exceed 32 hours TIS, repetitive inspections for cracks in blade shanks
at intervals not to exceed 400 hours TIS, and, as necessary, rework or
replace blades at intervals not to exceed 1,200 hours TIS. That action
was prompted by reports of cracks in blade shanks and clamps. That
condition, if not corrected, could result in loss of a blade due to
blade shank and clamp cracks, which could result in loss of aircraft
control.
Since the issuance of those ADs, the FAA has received reports of:
(1) 37 cracked blades in the past three years, including two blade
separations with one resulting in a fatal accident;
(2) 4 cracked blade clamps, including one blade separation;
(3) 5 blade separations from hub fatigue cracks (only found in HC-
8( )( ) series hubs).
The investigations into these occurrences revealed fatigue cracks
in the following parts/areas:
(1) blade internal bearing bore (corrosion at origin) and blade
retention radius;
(2) steel hub blade clamps; and
(3) steel hub blade retention radius (only found in HC-8( )( )
series hubs).
Additionally, the FAA has determined that the HC-(1,4,5,8)(2,3)(X,V)(
)-( ) Series steel hub propellers have similar loading and load paths
to the failed HC-8( )( ) series propellers and may develop fatigue
cracks.
The FAA has reviewed and approved the technical contents of
Hartzell Propeller Inc. Service Bulletin (SB) No. HC-SB-61-217,
Revision 1, dated July 11, 1997, that describes procedures for
fluorescent dye penetrant and eddy current inspections of the blade and
an optical comparator inspection of the blade retention area, and, if
necessary, replacement with serviceable parts. In addition, this SB
describes procedures for visual and magnetic particle inspection of the
blade clamp, dye penetrant inspection of the blade internal bearing
bore and, if necessary, replacement with serviceable parts. For all HC-
(1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, this SB describes an
additional visual and magnetic particle inspection of the hub, and, if
necessary, replacement with serviceable parts.
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 ADs 68-13-02, 68-19-04, 75-17-34, and 77-14-07 to require
initial and repetitive fluorescent dye penetrant and eddy current
inspections of the blade and an optical comparator inspection of the
blade retention area, and, if necessary, replacement with serviceable
parts. In addition, this AD requires an initial and repetitive visual
and magnetic particle inspection of the blade clamp, dye penetrant
inspection of the blade internal bearing bore and, if necessary,
replacement with serviceable parts. Also, for all HC-
(1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, this AD requires an
additional initial and repetitive visual and magnetic particle
inspection of the hub and, if necessary, replacement with serviceable
parts. Finally, this AD adds a reporting requirement to obtain
additional data and determine if adjustment can be made to the
repetitive inspection intervals, with possible relief. The actions are
required to be accomplished in accordance with the SB 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 96-ANE-40.'' 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.
[[Page 45311]]
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), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-614 (33 FR
9252, June 22, 1968), 39-868 (33 FR 12961, September 13, 1968), 39-868
(34 FR 18296, November 15, 1969), 39-2337 (40 FR 33433, August 8,
1975), and 39-2955 (42 FR 35638, July 11, 1977), and by adding a new
airworthiness directive, Amendment 39-10112, to read as follows:
97-18-02 Hartzell Propeller Inc.: Amendment 39-10112. Docket 96-ANE-
40. Supersedes AD 68-13-02, Amendment 39-614; AD 68-19-04, Amendment
39-868; AD 75-17-34, Amendment 39-2337; AD 77-14-07, Amendment 39-
2955.
Applicability: Hartzell Propeller Inc. ()HC-()(2,3)(X,V)()-()
series and HA-A2V20-1B series propellers with aluminum blades. These
propellers are installed on but not limited to the following
aircraft:
Manufacturer Aircraft Model
Aero Commander (Twin Commander)
500 AERO COMMANDER
500A AERO COMMANDER
500B, 500S, 500U AERO COMMANDER
520 AERO COMMANDER
560 AERO COMMANDER
560A, 560E AERO COMM.
680, 680E, 720 AERO COMM.
680F, FP, FL, FLR AERO COMMANDER
B1 (CALLAIR)
Aeromere
FALCO F.8.L
Aeronautica Macchi
AL60-F5
AM-3
Bauger
SAIL PLANE
Beech
35 SERIES BONANZA
35-C33 DEBONAIR
35-C33A, E33A, F33A
50 SERIES TWIN BONANZA
58P, 58TC BARON
95-55, 95-A55, 95-B55 BARON
65, A65, 65-(B)80, 65-A80, 70
A65-8200, 70
Bellanca
14-13
14-19
14-19-2
14-19-3
7GCA, 7GCB, 7GCC
DW-1 EAGLE
Camair
480
Cessna
170
170A
172 SKYHAWK
175
180, A, B, C, D, E, F, G, H
182, A, B, C, D, E
182F, G, H, J, K, L, M
210, A, B, C, 5, 5A
310, 310A
310B, 310C
310D, E, F, G, H, E310H
320, 320-1 SKYKNIGHT
320A, 320B
402 BUSINESSLINER
411
WREN 460
WREN 460H, J, K, L, M
deHavilland
DH104 DOVE
DH114 HERON
Dornier
DO27Q-6
DO28A-1
DO28B-1
Fuji
T-3, LM-2
GAF--Gov't. Aircraft Factories
N22B, N24A, N22S, N22C
Goodyear (Loral)
GA22A GOODYEAR BLIMP
GZ19, 19A GOODYEAR BLIMP
Great Lakes
2T-1A-2
Grumman
G44, G44A WIDGEON
G21C, D GOOSE
Helio
H-391 COURIER
H-391B COURIER
H-395A COURIER
Luscombe
11
11A
Mooney
M20
Multitech (Temco)
D16 TWIN NAVION
D16A TWIN NAVION
Nardi
FN-333
Navion
NAVION B
NAVION, NAVION A
Pacific Aerospace (Fletcher)
FU-24, FU-24A
Piaggio
P-149D
P136-L1 ROYAL GULL
P136-L2 ROYAL GULL
P149D
P166 ROYAL GULL
Pilatus
PC-3
PC-6; PC-6-H1, -H2 PORTER
Piper
PA-E23-250 AZTEC
PA14 FAMILY CRUISER
PA18(A)(S)-150 SUPER CUB
PA18A-150 SUPER CUB
PA22-150, PA22S-150
TRIPACER
PA23 SERIES APACHE
PA23-160 APACHE
PA23-235 AZTEC
PA23-250 AZTEC
PA24-250 COMANCHE
PA24-400 COMANCHE
PA24S COMANCHE
PA28 CHEROKEE
PA28-140 CHEROKEE
Prop Jets Inc.
200
200A,B,C
Republic (STOL Amphibian)
RC3 SEABEE
Scottish Aviation (BAE)
B.206 SERIES 2 BEAGLE
Stinson
L-5
108, -1, -2, -3
108-2-3
Sud Aviation (SOCATA)
GY.80-150 GARDAN
GY.80-160 GARDAN HORIZON
Swift
GC-1B
Taylorcraft
20
Texas Bullet
205
Windecker
EAGLE
Note 1: The above is not a complete list of aircraft which may
contain the affected Hartzell Propeller Inc. ()HC-()(2,3)(X,V)()-()
series and HA-A2V20-1B series propellers with aluminum blades
because of installation approvals made by, for example, Supplemental
Type Certificate or field approval under FAA Form 337 ``Major Repair
and Alteration.'' It is the responsibility of the owner, operator,
and person returning the aircraft to service to determine if an
aircraft has an affected propeller.
Note 2: The parenthesis that appear in the propeller models
indicate the presence or absence of additional letter(s) which vary
the basic propeller hub model designation. This airworthiness
directive is applicable regardless of whether these letters are
present or absent on the propeller hub model designation.
Note 3: This 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 request approval for an
alternative method of compliance in accordance with paragraph (g) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent blade separation due to cracked blades, hubs, or
blade clamps, which can result in loss of control of the airplane,
accomplish the following:
[[Page 45312]]
(a) On Hartzell propeller models with hub models ()HC-
(1,4,5,8)(2,3)(X,V)()-() perform initial and repetitive inspections
and, if necessary, replace with serviceable parts in accordance with
Hartzell Propeller Inc. Service Bulletin (SB) No. HC-SB-61-217,
Revision 1, dated July 11, 1997, as follows:
(1) Initially perform a fluorescent dye penetrant and eddy
current inspection of the blade, an optical comparator inspection of
the blade retention area, a dye penetrant inspection of the blade
internal bearing bore, and a visual and magnetic particle inspection
of the blade clamp and of the hub. The initial inspection is
required within the following:
(i) 1,000 hours time since new (TSN) for propellers with less
than 900 hours TSN on the effective date of this AD, provided that
the initial inspections are performed within 60 calendar months TSN
or 24 calendar months after the effective date of this AD, whichever
calendar time occurs later, or
(ii) 100 hours time in service (TIS) for propellers with 900 or
more hours TSN, or unknown TSN, on the effective date of this AD,
provided that the initial inspections are performed within 24
calendar months after the effective date of this AD.
(2) Thereafter, perform repetitive fluorescent dye penetrant and
eddy current inspection of the blade, an optical comparator
inspection of the blade retention area, and a visual and magnetic
particle inspection of the blade clamp. The repetitive inspection is
required at intervals not to exceed 500 hours TIS or 60 calendar
months, whichever occurs first, since last inspection.
(3) Thereafter, perform a repetitive visual and magnetic
particle inspection of the hub. This repetitive hub inspection is
required at intervals not to exceed 250 hours TIS or 60 calendar
months, whichever occurs first, since last inspection.
(4) Thereafter, perform a repetitive dye penetrant inspection of
the blade internal bearing bore. This repetitive blade internal
bearing bore inspection is required at intervals not to exceed 60
calendar months since last inspection.
(b) On Hartzell propeller models with hub models ( )HC-
(A,D)(2,3)(X,V) ( )-( ), and HA-A2V20-1B, except HC-A3VF-7( ),
perform initial and repetitive inspections and, if necessary,
replace with serviceable parts in accordance with Hartzell SB No.
HC-SB-61-217, Revision 1, dated July 11, 1997, as follows:
(1) Initially perform a fluorescent dye penetrant and eddy
current inspection of the blade, an optical comparator inspection of
the blade retention area, a visual and magnetic particle inspection
of the blade clamp, and a dye penetrant inspection of the blade
internal bearing bore. The initial inspection is required within the
following:
(i) 1,000 hours TSN for propellers with less than 800 hours TSN
on the effective date of this AD, provided that the initial
inspections are performed within 60 calendar months TSN or 24
calendar months after the effective date of this AD, whichever
calendar time occurs later, or
(ii) 200 hours TIS for propellers with 800 or more hours TSN, or
unknown TSN, on the effective date of this AD, provided that the
initial inspections are performed within 24 calendar months after
the effective date of this AD.
(2) Thereafter, perform repetitive fluorescent dye penetrant and
eddy current inspection of the blade, an optical comparator
inspection of the blade retention area, and a visual and magnetic
particle inspection of the blade clamp. The repetitive inspection is
required at intervals not to exceed 500 hours TIS or 60 calendar
months, whichever occurs first, since last inspection.
(3) Thereafter, perform repetitive dye penetrant inspections of
the blade internal bearing bore. This repetitive blade internal
bearing bore inspection is required at intervals not to exceed 60
calendar months since last inspection.
(c) On Hartzell propeller models with hub models HC-A3VF-7( )
perform initial and repetitive inspections and, if necessary,
replace with serviceable parts in accordance with Hartzell SB No.
HC-SB-61-217, revision 1, dated July 11, 1997, as follows:
(1) Initially perform a fluorescent dye penetrant and eddy
current inspection of the blade, an optical comparator inspection of
the blade retention area, a visual and magnetic particle inspection
of the blade clamp, and a dye penetrant inspection of the blade
internal bearing bore. The initial inspection is required within the
following:
(i) 3,000 hours TSN for propellers that have never been
overhauled and have less than 2,500 hours TSN on the effective date
of this AD, provided that the initial inspections are performed
within 60 calendar months TSN or 24 calendar months after the
effective date of this AD, whichever calendar time occurs later, or
(ii) 3,000 hours TIS since last overhaul for propellers that
have been overhauled but have less than 2,500 hours TIS since last
overhaul on the effective date of this AD, provided that the initial
inspections are performed within 60 calendar months TIS since last
overhaul or 24 calendar months after the effective date of this AD,
whichever calendar time occurs later, or
(iii) 500 hours TIS, for propellers that have never been
overhauled and have 2,500 or more hours TSN on the effective date of
this AD, or propellers which have been overhauled and have 2,500 or
more hours TIS since last overhaul on the effective date of this AD,
or propellers with unknown TSN, provided that the initial
inspections are performed within 24 calendar months after the
effective date of this AD.
(2) Thereafter, perform repetitive fluorescent dye penetrant and
eddy current inspection of the blade, an optical comparator
inspection of the blade retention area, and a visual and magnetic
particle inspection of the blade clamp. The repetitive inspection is
required at intervals not to exceed 3000 hours TIS or 60 calendar
months, whichever occurs first, since last inspection.
(3) Thereafter, perform repetitive dye penetrant inspections of
the blade internal bearing bore. This repetitive blade internal
bearing bore inspection is required at intervals not to exceed 60
calendar months since last inspection.
(d) The initial inspection of the internal blade bearing bore
required by paragraphs (a)(1), (b)(1), or (c)(1) of this AD need not
be accomplished again if previously accomplished in accordance with
page 4 of Hartzell SB No. HC-SB-61-217, Revision 1, dated July 11,
1997.
(e) If not previously accomplished, shot peen the propeller
blade shank area during the initial inspection required by
paragraphs (a)(1), (b)(1), or (c)(1), as appropriate, and perform
the shot peening in accordance with Hartzell SB No. HC-SB-61-217,
Revision 1, dated July 11, 1997. Re-shot peening of the propeller
blade shank area during the repetitive inspections required by
paragraphs (a)(2), (b)(2), or (c)(2), as appropriate, is required
only if the propeller blade shank area has been repaired or has
excessive wear or damage in accordance with Hartzell SB No. HC-SB-
61-217, Revision 1, dated July 11, 1997.
(f) Report inspection results to the Manager, Chicago Aircraft
Certification Office, FAA, Small Airplane Directorate, 2300 East
Devon Ave., Des Plaines, IL 60018, within 15 working days of the
inspection. Reporting requirements have been approved by the Office
of Management and Budget (OMB) and assigned OMB control number 2120-
0056.
(g) 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, Chicago Aircraft Certification
Office. The request should be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Chicago Aircraft Certification Office.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Chicago Aircraft Certification
Office.
(h) 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.
(i) The actions required by this AD shall be done in accordance
with the following Hartzell Propeller Inc. SB:
----------------------------------------------------------------------------------------------------------------
Document No. Revision Pages Date
----------------------------------------------------------------------------------------------------------------
HC-SB-61-217................................ 1 1-16 July 11, 1997.
Total pages: 16.
----------------------------------------------------------------------------------------------------------------
[[Page 45313]]
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 Hartzell Propeller Inc., One
Propeller Place, Piqua, OH 45356-2634, ATTN: Product Support;
telephone (937) 778-4200, fax (937) 778-4321. 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.
(j) This amendment becomes effective on September 11, 1997.
Issued in Burlington, Massachusetts, on August 15, 1997.
James C. Jones,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 97-22677 Filed 8-26-97; 8:45 am]
BILLING CODE 4910-13-P
