Federal Register Information
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Amendment 39-5414; AD 85-14-10 R2
HARTZELL PROPELLER PRODUCTS DIVISION Models ( )HC- ( )( )(X,V) Series Propellers
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85-14-10 R2 HARTZELL PROPELLER PRODUCTS DIVISION: Amendment
39-5098, as amended by 39-5334, is further amended by Amendment
39-5414. Applies to all Hartzell Model ( )HC- ( )( )(X,V) series
propellers with Hartzell Part Number C-3-( ) blade clamp assemblies.
Compliance required within the next 60 days after the effective date of Amendment 39- 5414, unless already accomplished.
To prevent propeller blade clamp failure, accomplish the following:
(a) Replace all propeller blade clamp assemblies which have serial
numbers ranging from 0 through D5293 with airworthy clamp assemblies,
or inspect as follows:
(1) Visually inspect the internal, inboard radius area of the clamp,
especially next to the clamp bolt hole, for corrosion. Remove from
service all clamps showing signs of corrosion (rework is not permitted)
and replace with airworthy clamp assemblies.
(2) Magnetic particle inspect all internal and external surfaces
of the clamp for evidence of cracks in accordance with Hartzell
Specification No. H-S-7 dated August 4, 1981, or FAA approved
equivalent. Replace all cracked clamps with airworthy clamp assemblies.
(3) Penetrant inspect all external surfaces of the blade clamp
assemblies within 100 hours since inspection in Paragraphs (a)(1) and
(2) above and at intervals not to exceed 100 hours since last
inspection. Replace all clamps showing signs of cracks with airworthy
(b) Replace all propeller blade clamp assemblies which have
mismatching serial numbers on each clamp half or which have unreadable
serial numbers with airworthy clamp assemblies.
(c) Accomplish the following on all blade clamp assemblies which have
serial numbers ranging from D5294 through K6336 in accordance with
Hartzell Service Instruction No. 159B dated May 23, 1986, or FAA
(1) Using a 10x power magnifying glass, visually inspect the inner
bearing race radius, especially next to the inner clamp bolt hole, for
defects in the form of corrosion, tool marks, gouges, scratches, etc.
(2) Remove all evidence of defects in the clamp inner bearing race
radius. Replace all reworked clamps that exceed the rework limitations
defined in the Service Instruction with airworthy clamp assemblies or
return to Hartzell for further evaluation.
(3) Magnetic particle inspect the clamp for evidence of cracks. Replace all cracked clamps with airworthy clamp assemblies.
(4) Replate all reworked clamps.
NOTE: Compliance with Amendment 39-5098 constitutes compliance with this AD.
Aircraft may be ferried in accordance with the provisions of Federal
Aviation Regulations 21.197 and 21.199 to a base where the AD can be
Upon request, an equivalent means of compliance with the
requirements of this AD may be approved by the Manager, Chicago
Aircraft Certification Office, FAA, Central Region.
Hartzell Service Instruction No. 159B dated May 23, 1986, and
Hartzell Specification No. H-S-7 dated August 4, 1981, are incorporated
herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All
persons affected by this directive who have not already received these
documents from the manufacturer may obtain copies upon request to
Hartzell Propeller Products Division, TRW Aircraft Components Group,
350 Washington Avenue, Piqua, Ohio 45356. These documents also may be
examined at the Office of Regional Counsel, FAA, Attn: Rules Docket No.
84-ANE-24, 12 New England Executive Park, Burlington, Massachusetts
01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30
This amendment amends Amendment 39-5098, (50 FR 30417), AD
85-14-10, as amended by Amendment 39-5334, (51 FR 23732), AD 85-14-10
This amendment, 39-5414, becomes effective on September 25, 1986.