AD 86-07-02 R1

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AD Number:
86-07-02 R1
Document Type:
AD Final Rules
Docket Number:
86-CE-23-AD
Subject Heading:
Airworthiness Directives; Pilatus Model BN2A MK. 111, BN2A MK. 111-2, and BN2A MK. 111-3 Series Airplanes
Subject:
Main Landing Gear Torque Link Lug & Upper Case Inspection
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/28/1997
Make:
B-N Group Ltd.
Model:
BN2A MK. III | BN2A MK. III-2 | BN2A MK. III-3
Product Type:
Aircraft
Product Subtype:
Small 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Superseded AD: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Superseded By: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: 86-07-02 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   86-CE-23-AD

AMENDMENT:   39-10171

AD NUMBER:   86-07-02 R1

SUBJECT HEADING:   Airworthiness Directives; Pilatus Model BN2A MK. 111, BN2A MK. 111-2, and BN2A MK. 111-3 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 28, 1997.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
86-07-02 R1 PILATUS BRITTEN-NORMAN LTD: Amendment 39-10171; Docket No. 86-CE-23-AD. Revises AD 86-07-02, Amendment 39-5382.

Applicability: Models BN2A MK. 111, BN2A MK. 111-2, and BN2A MK. 111-3 airplanes (all serial numbers), certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required prior to further flight after the effective date of this AD (see NOTE 2) or within 100 hours time-in-service (TIS) after the last inspection accomplished in accordance with AD 86-07-02, whichever occurs later, and thereafter at intervals not to exceed 100 hours TIS.

NOTE 2: The "prior to further flight after the effective date of this AD" compliance time was the original initial compliance time of AD 86-07-02, and is being retained to provide credit and continuity for already-accomplished and future inspections.

To prevent failure of the main landing gear caused by cracks in the torque link assembly area, which could lead to loss of control of the airplane during landing operations, accomplish the following:

(a) Inspect the junction of the torque link lug and upper case for cracks (using a 10- power magnifying glass or by dye penetrant methods) in accordance with Fairey Hydraulics Limited Service Bulletin (SB) 32-7, Issue 3, dated January 30, 1990; or Fairey Hydraulics SB 32- 10, Issue 2, dated November 10, 1992, as applicable. Pilatus Britten-Norman SB BN-2/SB. 173, Issue 3, dated November 16, 1990, references Fairey Hydraulic Limited SB 32-7; and Pilatus Britten-Norman SB BN-2/SB.209, Issue 1, dated November 30, 1992, references Fairey Hydraulic Limited SB 32-10.

(b) If cracked parts are found during any of the inspections required by this AD, prior to further flight, replace the cracked parts with airworthy parts in accordance with the applicable maintenance manual.

(c) If the landing gear is replaced, only equal pairs of the same manufacturer are approved as replacement parts. Mixing of different manufacturer landing gears is not authorized.

(d) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these actions along with other scheduled maintenance on the airplane.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the inspection requirements of this AD can be accomplished.

(f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, Missouri 64106.

(1) The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate.

(2) Alternative methods of compliance approved for AD 86-07-02 are considered approved as alternative methods of compliance for this AD.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate.

(g) The inspections required by this AD shall be done in accordance with Fairey Hydraulics Limited Service Bulletin 32-7, Issue 3, dated January 30, 1990, or Fairey Hydraulics Service Bulletin 32-10, Issue 2, dated November 10, 1992, as applicable. 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 Fairey Hydraulics Limited, Claverham, Bristol, England; or Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, United Kingdom PO35 5PR. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(h) This amendment (39-10171) revises AD 86-07-02, Amendment 39-5382.

(i) This amendment becomes effective on November 28, 1997.

FOOTER: