AD 81-18-06

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AD Number:
81-18-06
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild Model C-119 Series Airplanes
Subject:
Aileron Control System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
08/31/1981
Effective Date:
09/10/1981
Make:
Aero Union Corporation | Hawkins & Powers Aviation Inc. | Starbird Inc. | Waara William | Pacific In...Show more
Model:
C-119C | C-119G | C-119G-3E | C-119F/R4Q2 | C-119L
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
AIR-700: Compliance & Airworthiness Division
Office of Primary Responsibility:
AIR-720: Operational Safety Branch
CFR Part Reference:
Part 39
Comments:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 81-18-06
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4202

AD NUMBER:   81-18-06

SUBJECT HEADING:   Airworthiness Directives; Fairchild Model C-119 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 10, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
81-18-06 FAIRCHILD: Amendment 39-4202. Applies to Model C-119 series airplanes certificated in all categories under various type certificates including, but not limited to Pacific International Foods, Inc., A6NW, William Waara, A32CE, Starbird, Inc., A5NW, Aero Union Corporation, A21WE, Hawkins and Powers, Inc., A24WE.

Compliance required as indicated, unless already accomplished.

To prevent possible wing failure due to loads induced by a free aileron, accomplish the following:

(a) Within 100 hours' time in service or within 60 days from the effective date of this AD, whichever occurs earlier, conduct inspections of the inboard and outboard aileron, aileron control system, and all aileron attachment fittings of the outer wing panel using the applicable inspection instructions of Section III Wing Group and Section X Control Systems Group of USAF Technical Order T.O. 1C-119G-36 and additional inspection procedures given below.

(b) Remove the left and right hand inboard and outboard ailerons and inspect for evidence of cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear and elongated holes in accordance with the visual, dye penetrant and X-ray procedures of TO.O 1C-119G-36, paragraphs 3-25 through 3-36.

(c) Inspect the aileron flight control linkage in the left and right hand wing outer panel for evidence of cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear and elongated holes in accordance with visual, magnetic and dye penetrant procedures of T.O. 1C-119G-36, paragraphs 10-11 through 10-14, with the following exceptions for the bellcrank item C-30 of T.O. 1C-119G-36.

(1) Remove the left and right hand inboard aileron bellcrank assembly, P/N 110-727202-21 and P/N 110-727202-22, indicated as item C-30 in T.O. 1C-119G-36, Figure 10-3, page 10-25.

(2) Conduct a dye penetrant inspection in accordance with T.O. 1C-119G-36, paragraph 10-14(c)(2), after removal of the bushings and bearings. Particular attention should be directed to the exterior and interior surfaces of the central hub of the bellcrank.

(d) Using a 10X magnifier, inspect the truss support assembly which is attached to the upper and lower rear wing spar cap and inner aileron bellcrank inter-rib support bracket in left and right outer wing panels for evidence of corrosion, cracks or loss of structural integrity caused by erosion of tubular wall thickness.

NOTE: Part numbers found on some C-119 model aircraft are P/N 78-135106-0005R and P/N 78-135106-0008L.

(e) If any cracks, corrosion, pitting; loose, distorted or corroded fasteners; excessive wear or elongated holes are detected during the inspections, repair in accordance with T.O. 1C-119B-3 or replace with like serviceable part in accordance with the procedures of the applicable paragraphs in T.O. 1C-119G-36, prior to further flight.

(f) Prior to return to service, after accomplishing other inspections required by this AD, conduct a balance inspection of all four ailerons per procedures specified in the applicable maintenance instructions. Any out-of-limit condition must be corrected prior to further flight.

(g) Repeat the inspections required by paragraph (c), (d) and (f) of this AD at intervals not to exceed 3000 hours' time in service or one (1) year from the last such inspection, whichever occurs earlier.

(h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD.

(i) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region.

(j) The specifications and procedures identified and described in this directive 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 may obtain copies upon request to FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office.

This amendment becomes effective September 10, 1981.

FOOTER: