[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]


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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.

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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: ``9-ad-
[email protected]''. 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