AD 69-08-01

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AD Number:
69-08-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Fairchild-Hiller Model F-27 and FH-227 Airplanes
Subject:
Horizontal Stabilizer
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/16/1969
Make:
Maryland Air Industries, Inc.
Model:
F-27 | F-27A | F-27B | F-27F | F-27G | F-27J | F-27M | FH-227 | FH-227B | FH-227C | FH-227D | FH-227E
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 69-08-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-745

AD NUMBER:   69-08-01

SUBJECT HEADING:   Airworthiness Directives; Fairchild-Hiller Model F-27 and FH-227 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 16, 1969.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-08-01 FAIRCHILD-HILLER: Amdt. 39-745. Applies to F-27 type and FH-227 type airplanes certificated in all categories and incorporating horizontal stabilizer rear spar fittings, P/N 27-210501-3, -4, -5, or -6.

Compliance required as indicated.

To detect cracks in the horizontal stabilizer rear spar fittings, accomplish the following:

(a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 300 hours' time in service after the last inspection comply with (b).

(b) Inspect for cracks all four horizontal stabilizer rear spar fittings, P/N 27-210501-3, -4, -5, and -6, using a penetrant method with a glass of at least 10 power. Particular attention should be given to cracks originating from the lower bolt hole for the elevator inboard hinge truss support on the fore and aft leg of the outboard fitting (P/N's 27-210501-5 and -6; refer to Figure 3, Section 55-4 of Fairchild Hiller Illustrated Parts Catalog). It is not necessary to remove the bolts to perform this inspection. Replace cracked parts before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be performed.

(c) The inspections required by (a) need not be accomplished when all four Fairchild Hiller fittings, P/N 27-210501-13, -14, -15, and -16, are incorporated. When replacing fittings, shim clearance between the truss assembly support tube bushings and fittings, as close to zero as possible.

(d) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.

(Fairchild Hiller Service Bulletins No. F27-55-17 and FH-227-55-7, both dated February 10, 1969, cover this subject).

This amendment is effective April 16, 1969.

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