AD 87-09-01

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AD Number:
87-09-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Messerschmitt-Bolkow-Blohm Model BO-209-150FV, -150RV, -160FV, -160RV, an...Show more
Subject:
Wing Spar Carry-Through
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/06/1987
Make:
DaimlerChrysler Aerospace AG
Model:
BO-209-150 FF | BO-209-150 FV | BO-209-150 RV | BO-209-160 FV | BO-209-160 RV
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Superseded AD: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Superseded By: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: 87-09-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5616

AD NUMBER:   87-09-01

SUBJECT HEADING:   Airworthiness Directives; Messerschmitt-Bolkow-Blohm Model BO-209-150FV, -150RV, -160FV, -160RV, and -150FF "MONSUN" Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 6, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-09-01 MESSERSCHMITT-BOLKOW-BLOHM GmbH (MBB): Amendment 39-5616. Applies to Models BO-209-150FV, -150RV, -160FV, -160RV, and -150FF "MONSUN" airplanes (all serial numbers) certificated in any category.

Compliance: Required as indicated after the effective date of this AD, unless already accomplished.

To preclude inflight wing separation, accomplish the following:

(a) Before further flight:

(1) Inspect and modify the wing spar carry-through lower cap strip in the fuselage area in accordance with the "Inspection of Wing Spar Carry-Through" paragraph of MBB Technical Instruction No. 209-1/87, dated January 26, 1987 (hereinafter referred to as MBB TI No. 209-1/87), and the manufacturer's maintenance manual procedures, as follows:

(i) Jack up the airplane and remove both main landing gear struts.

(ii) Remove both landing gear brackets, Part Number (P/N) 209-21233 and P/N 209-21243.

(iii) Drill out the rivets (four each) on each side of the right and left-hand elongated holes (the passage for the landing gear strut through the wing spar carry-through).

(iv) Examine the surface quality adjacent to each elongated hole and the associated four rivet holes, and remove any visible flutes or score marks by polishing.

(v) Carry out an ultrasonic test of the area adjacent to the elongated holes for cracks. If any crack is detected, accomplish paragraph (b) of this AD.

(vi) Carry out an eddy current test of the area adjacent to the associated rivet holes for cracks. If any crack is detected, accomplish paragraph (b) of this AD.

(vii) Modify the four rivet holes adjacent to each of the above-mentioned elongated holes by reaming out the rivet holes, consolidating the rivet hole walls, re-reaming the holes, and inserting HI-LOK helical rivets, in accordance with instructions contained in MBB TI No. 209-1/87.

(viii) Reinstall the landing gear brackets, P/N 209-21233 and P/N 209-21243.

(ix) Replace unserviceable rubber bearings, P/N 209-51003.02, with new serviceable parts.

(x) Reinstall the main landing gear struts.

CAUTION: During reinstallation of the struts, scoring of the surface adjacent to the elongated holes of the spar carry-through must be avoided. If scoring damage occurs, repeat steps (a)(1)(iv) through (a)(1)(vi) of this AD.

(2) Carry out an ultrasonic test for cracks in the transition radii of the fuselage mounted wing attachment brackets in accordance with instructions contained in MBB TI No. 209-1/87. If any crack is detected, accomplish paragraph (b) of this AD.

(3) Visually inspect for cracks or deformation of the forward and aft frame plates which form the forward and aft metal webs of the wing spar carry-through in the adapter structure to the wing stub in accordance with instructions contained in MBB TI No. 209-1/87. If any crack is detected, accomplish paragraph (b) of this AD.

(4) The inspection, corrective action, and modification specified in paragraph (a) of this AD must be performed at an appropriately rated FAA repair station by personnel specifically training by MBB.

(b) If any crack is detected, before further flight, accomplish the following:

(1) Inform the manufacturer at the address listed below of the crack(s) found.

(2) Request a manufacturer repair procedure approved by the FAA.

(3) Incorporate the FAA approved repair procedures.

(c) Prior to further flight:

(1) Change the "LIMITATIONS" section of the FAA approved Model BO-209 "MONSUN" Approved Flight Manual (AFM) using pen and ink, and operate the airplane in accordance with these limitations as follows:

(i) Paragraph 2.9.2 of the AFM, change "above" to "up to," to read as follows: "Utility Category: Spinning with flaps retracted, lazy eights, chandelles, steep turns up to 60 degree bank."

(ii) Paragraph 2.12.9 of the AFM, change "above" to "up to" in Section 2. "Utility Category" to read as follows: "2. Utility Category ... lazy eight up to 60 degree bank ..."

(2) Fabricate and install on the canopy center line strip, visible to the pilots, the following placard using letters of a minimum 0.10 inch in height: "ACROBATIC FLIGHT PROHIBITED".

(3) Modify the limitations placard mounted on the canopy center line strip by permanently deleting or obliterating the following words: "Only if accelerometer is installed: Slow roll 125 Kt, wing over, loop 135 Kt, steep turns above 60 degree bank 117 Kt."

NOTE: The placard required by paragraph (c)(2) of this AD may be mounted in a suitable manner to cover the above-stated text to satisfy this requirement.

(d) Upon accumulating 3000 hours time-in-service (TIS) and every 500 hours TIS thereafter, carry out an ultrasonic test of the wing spar carry-through lower cap strip area adjacent to the elongated holes and the associated four rivet holes with HI-LOK rivets for cracks in accordance with the MBB Technical Note 209-1/87, page 3, dated January 22, 1987. If any crack is detected, before further flight, accomplish the repairs specified in paragraph (b) of this AD.

(e) If a ferry flight to an approved maintenance location is required:

(1) Airplanes not previously used for acrobatics may be flown to the location in accordance with FAR 21.197.

(2) Airplanes previously used for acrobatics must be visually inspected for cracks prior to the ferry flight in accordance with the "sketch" (page 4 of 4) of the MBB Technical Note No. 209-1/87, dated January 22, 1987. If any crack is found, further flight is prohibited until all actions of paragraphs (a) and (b) of this AD are accomplished.

(f) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium.

All persons affected by this directive may obtain copies of the documents referred to herein upon request to Messerschmitt-Bolkow-Blohm GmbH, Department 1QS 143, Post fach 801160, D-8000 Munchen 80, Federal Republic of Germany; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment, 39-5516, becomes effective on May 6, 1987.

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