Hartzell Prop AD PDF Print E-mail
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Saturday, 25 August 2007 16:26

TO PREVENT BLADE SEPARATION DUE TO CRACKED BLADES, HUBS, OR BLADE
CLAMPS, WHICH CAN RESULT IN LOSS OF,CONTD.
97-18-02
HARTZELL PROPELLER INC.

Amendment 39-10112

Docket No. 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:
Aero Commander (Twin Commander): 500; 500A; 500B, 500S, 500U; 520; 560;
560A, 560E; 680, 680E, 720; 680F, 680FP, 680FL, 680FLR; 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; 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, F, G, H, J, K, L, M; 210, A, B, C, 5, 5A; 310, A, B, C; D, 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:

(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. Pages DateHC-SB-61-217 1-16 July 11, 1997
Total pages: 16.

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.

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.

Last Updated on Sunday, 26 August 2007 17:03
 

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