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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Amendment 39-6271; AD 81-13-06 R2

HAMILTON STANDARD: Hydromatic (noncounterweighted) propellers with aluminum blades



Preamble Information

Regulatory Information

81-13-06 R2 HAMILTON STANDARD: Amendment 39-4133 as revised by Amendment 39- 4409 is further revised by Amendment 39-6271.

Applicability: Hamilton Standard Hydromatic (noncounterweighted) propellers with aluminum blades that use engine oil for pitch control (does not apply to propellers with integral oil control or to propellers with steel blades) of the following types: 22D30, 22D40, 23D40, 23E50, 23E60, 24D50, 24E60, 33D50, 33E60, 34D50, 34D51, 34E60, 43D50, 43D51, 43E60, and 43H60, as installed on various reciprocating engine powered aircraft such as, but not limited to: Beech D17 and D18, Boeing 377 series, Canadair Model 4 and CL-215, Curtiss-Wright C-46, DeHavilland DHC-2, DHC-3, and DHC-4, General Dynamics (Convair) T-29, 240, 340, and 440 series, Gulfstream American (Grumman) G-12A, G164, F4U, S-2F, TBM, and W-2F series, Lockheed L-10, L-12, 049, 749, 1049, 1649 series, Martin 202 and 404 series, McDonnell Douglas B-26, DC-3, DC-4, DC-6, and DC-7 series, North American AT-6, B-25, P-51, SNJ-5, T-6 and T-28.

Compliance: Required as indicated, unless already accomplished.

To prevent propeller blade failure due to corrosion and fatigue, accomplish the following:

(a) Inspect propeller blades within the next 90 days after July 1, 1982, or within 18 months since last inspection, whichever occurs later, for corrosion in the blade fillet and shank area, particularly under the teflon friction reduction strip and the resin corrosion barrier, in accordance with Hamilton Standard Aluminum Blade Overhaul Manual No. 130B, dated March 1, 1980, previously incorporated by reference on June 28, 1982, in AD 81-13-06. Thereafter, if corrosion is found reinspect at intervals not to exceed 18 months since the last inspection.

(b) For propellers with all installed blades having no corrosion at the last inspection, the 18 month reinspection interval may be increased as follows:

(1) Reinspect between 33 and 39 months since the last inspection. If corrosion is found to be beyond repairable limits return to the 18 month reinspection interval required by paragraph (a). If corrosion is found to be within repairable limits the reinspection interval cannot exceed a 36 month reinspection schedule.

(2) If no corrosion is found at the last 33 to 39 month reinspection in accordance with paragraph (b)(1), then thereafter reinspect at intervals not to exceed 60 months. If corrosion is found to be beyond repairable limits at any reinspection interval return to the 18 month reinspection interval required by paragraph (a). If corrosion is found to be within repairable limits the reinspection interval may remain on a schedule not to exceed 60 months.

(c) Prior to further flight, blades with corrosion in the fillet or shank area must be replaced with an airworthy blade or repaired in accordance with Hamilton Standard Aluminum Blade Overhaul Manual No. 130B, dated March 1, 1980.

(d) Disassembled propeller blades preserved in accordance with Hamilton Standard Aluminum Blade Overhaul Manual No. 130B, dated March 1, 1980, need not include storage time when computing the time since last inspection.

(e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, may adjust the compliance times specified in this AD or approve an equivalent means of compliance with this AD.

NOTE: Extensions to the compliance schedule previously granted to owners/operators are still applicable to this amendment. These extensions which are beyond a 39 month reinspection interval may be extended to 60 months as provided in paragraph (b)(2).

(f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspection required by this AD.

This AD revises AD 81-13-06 R1, Amendment 39-4409, (47 FR 36217; August 19, 1982), which revised AD 81-13-06, Amendment 39-4133.

This amendment (39-6271, AD 81-13-06 R2) becomes effective on September 15, 1989


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