AD 69-24-02 R3

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AD Number:
69-24-02 R3
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BEECH Model 99 Series Airplanes
Subject:
Maximum Speed
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/11/1983
Make:
Textron Aviation Inc.
Model:
99 | 99A | 99A (FACH) | A99 | A99A | B99 | C99
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Superseded AD: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Superseded By: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: 69-24-02 R3
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4607

AD NUMBER:   69-24-02 R3

SUBJECT HEADING:   Airworthiness Directives; BEECH Model 99 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 11, 1983.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
69-24-02 R3 BEECH: Amendment 39-879 as amended by Amendment 39-1222 is further amended by Amendment 39-4240 and Amendment 39-4607. Applies to all Beech 99 series (Serial Numbers U-1 thru U-49, U-51 thru U-131, U-133 thru U-145, and U-147) airplanes certificated in any category. EXCEPTIONS: Airplanes on which the elevator control system has been modified in accordance with optional Beech Kit 99-5011 or Kit 99-5014 are required to comply with paragraph C only.

Compliance: Required as indicated, unless already accomplished.

To prevent an unsafe condition, effective immediately, restrict the aircraft to a maximum speed of 174 knots Vmo and remark the airspeed aircraft to a maximum speed of 174 knots Vmo and remark the airspeed indicator at that speed until the following are accomplished:

A. (1) Check for correct elevator control system rigging and if necessary, rerig in accordance with Beech Service Instruction 0309-364.

(2) Subsequent to the requirements of Paragraph A(1), conduct a flight test in accordance with flight test procedures contained in Beech Service Instruction 0309-364, or equivalent procedures approved by the Manager, Aircraft Certification Branch, FAA, Central Region.

B. On or before March 15, 1970, limit the upward travel of the leading edge of the stabilizer to a maximum of 3-1/2 degrees in accordance with Beech Service Instruction 0285-364 or Beech Service Instruction 0309-364. The downward travel of the stabilizer leading edge remains unchanged.

C. (1) On or before March 15, 1970, (a) install an aural warning device which indicates that the stabilizer trim system is in motion, (b) install an out-of-trim warning system indicating that the aircraft is out-of-trim longitudinally prior to takeoff, (c) install a newly designed standby trim switch and guards to prevent inadvertent operation, and (d) revise the electrical circuitry to prevent unwanted circuit breaker activation in the event that pilot and co- pilot simultaneously call for opposite trim. These modifications must be accomplished in accordance with instructions and procedures set forth in Beech Service Instruction 0270-350 or equivalent modifications approved by the Manager, Aircraft Certification Branch, FAA, Central Region.

(2) On or before March 15, 1970, relocate the trim release switch on the control wheel to make it more readily accessible to the crew, in accordance with instructions and procedures set forth in Beech Service Instruction 0249-156, or an equivalent method approved by the Manager, Aircraft Certification Branch, FAA, Central Region.

(3) On or before March 15, 1970, revise Beech Model 99 Approved Airplane Flight Manual by incorporating revision C-1 dated November 14, 1969, and revise Beech Model 99A Approved Airplane Flight Manual by incorporating revision A-5 dated November 14, 1969.

NOTE: When the revisions to the Approved Airplane Flight Manuals have been incorporated as required by paragraph C(3), the temporary amendments to the Airplane Flight Manuals in AD 69-18-06, as amended, may be deleted.

D. When paragraphs A and B of this AD have been accomplished, the aircraft may be operated at a maximum speed not to exceed 200 knots Vmo. When the modifications required by paragraphs A, B, and C of this AD have been accomplished, the aircraft may be operated at a speed not to exceed 226 knots Vmo.

E. Paragraphs A(1) and A(2) of this AD must be complied with irrespective of the speed limitation whenever the elevator control system is repaired or otherwise modified or the elevators are repaired or replaced.

AD 69-24-02, Amendment 39-879, superseded AD 69-18-06 as amended insofar as it changes the maximum speed restrictions provided in AD 69-18-06 as amended.

Amendment 39-879 became effective December 5, 1969, for all persons except those to whom it was made effective by first class letter dated November 21, 1969.

Amendment 39-1222 became effective June 3, 1971.

Amendment 39-4240 became effective October 16, 1981.

This Amendment 39-4607 becomes effective April 11, 1983.

FOOTER: