AD 93-11-04

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AD Number:
93-11-04
Document Type:
AD Final Rules
Docket Number:
92-NM-195-AD
Subject Heading:
Airworthiness Directives; FOKKER Model F27 Series Airplanes
Subject:
Outer Flap Center Hinge
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/22/1993
Make:
Fokker Services
Model:
F27 Mark 100 | F27 Mark 200 | F27 Mark 300 | F27 Mark 400 | F27 Mark 500 | F27 Mark 600 | F27 Mark 700
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Superseded AD: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Superseded By: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: 93-11-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   92-NM-195-AD

AMENDMENT:   39-8595

AD NUMBER:   93-11-04

SUBJECT HEADING:   Airworthiness Directives; FOKKER Model F27 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 22, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-11-04 FOKKER: Amendment 39-8595. Docket 92-NM-195-AD.
Applicability: Model F27 series airplanes (except Model F27 Mark 050 series airplanes); serial numbers 10102 and 10105 through 10240, inclusive; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent premature failure of the outer flap center hinge due to fatigue, which could result in reduced structural integrity of the outer flap, accomplish the following:

(a) For airplanes on which Fokker Service Bulletin SBF27/57-22 has not been accomplished and that have accumulated 72,000 or more total landings as of the effective date of this AD: Within 1,000 landings or 6 months after the effective date of this AD, whichever occurs first, perform a high frequency eddy current inspection of the outer flap center hinges to detect cracks, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991.

(1) If no crack is found, repair the outer flap center hinge within 2,800 landings or 2 calendar years following the inspection required by paragraph (a) of this AD, whichever occurs first, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991.

(2) If any crack is found, repair the outer flap center hinge, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991, at the times specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD.

(i) If the crack length inside the bore is less than 5 mm, and if no crack is found on any of the faces around the bore: Repair within 300 landings following the inspection required by paragraph (a) of this AD.

(ii) If the crack length inside the bore is equal to or more than 5 mm; or if the crack length inside the bore is less than 5 mm, and the crack is also present in one of the faces around the bore: Repair prior to further flight.

(b) For airplanes on which Fokker Service Bulletin SBF27/57-22 has been accomplished and that have accumulated 55,000 or more total landings as of the effective date of this AD: Within 1,000 landings or 6 months after the effective date of this AD, whichever occurs first, perform a high frequency eddy current inspection of the outer flap center hinges to detect cracks, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991.

(1) If no crack is found, repair the outer flap center hinge within 2,800 landings or 2 calendar years following the inspection required by paragraph (b) of this AD, whichever occurs first, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991.

(2) If any crack is found, repair the outer flap center hinge in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin F27/57-66, dated October 11, 1991, at the times specified in paragraph (b)(2)(i) or (b)(2)(ii) of this AD.

(i) If the crack length inside the bore is less than 5 mm, and if no crack is found on any of the faces around the bore: Repair within 300 landings following the inspection required by paragraph (b) of this AD.

(ii) If a crack inside the bore is located on the grease nipple bore half of the hinge; or if the crack length inside the bore is equal to or more than 5 mm; or if the crack length inside the bore is less than 5 mm and the crack is also present in one of the faces around the bore: Repair prior to further flight.

(c) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(e) The inspections and repairs shall be done in accordance with Fokker Service Bulletin F27/57-66, dated October 11, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(f) This amendment becomes effective on July 22, 1993.

FOOTER: