AD 86-26-02

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AD Number:
86-26-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; 86-26-02 Mitsubishi Model MU-2B-10, -15, -20, -25, -26, -26A, -30, -35, -...Show more
Subject:
POH/AFM Appendix - Icing
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/31/1986
Make:
Mitsubishi Heavy Industries, Ltd.
Model:
MU-2B-10 | MU-2B-15 | MU-2B-20 | MU-2B-25 | MU-2B-26 | MU-2B-26A | MU-2B-30 | MU-2B-35 | MU-2B-36 | ...Show more
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Superseded AD: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Superseded By: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: 86-26-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5498

AD NUMBER:   86-26-02

SUBJECT HEADING:   Airworthiness Directives; 86-26-02 Mitsubishi Model MU-2B-10, -15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 31, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   86-26-02 MITSUBISHI HEAVY INDUSTRIES, LTD. and MITSUBISHI AIRCRAFT INTERNATIONAL, INC.: Amendment 39-5498. Applies to Models MU-2B-10, -15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60 (all serial numbers) airplanes certificated in any category.

Compliance: Required within the next 100 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished.

To prevent engine flameout when in or departing an icing environment, accomplish the following:
(a) Modify the airplanes not equipped with manual ignition switches.
(1) For MU-2B-10, -15, -20, -25, -26 (S/N 008 through 347 except S/N 313, 321), -30, -35, and -36 (S/N 501 through 696 except S/N 652, 661), modify the airplane as described in MHI SR 066B dated November 13, 1986, Instructions 1.0 through 8.0. Compliance with GTEC S/B TPE/TSE 331-74-0003 is optional.
(2) For MU-2B-25, -26, -26A (S/Ns 313SA, 321SA, 348SA through 364SA, and 366SA through 394SA), -35, and -36A (S/Ns 652SA, 661SA, 697SA through 699SA and 701SA through 730SA), modify the airplane as described in MAI SR 040/74-001, Revision A, dated December 11, 1986, Accomplishment Instructions paragraphs A-G. Compliance with GTEC S/B TPE/TSE 331-74-0003 is optional.

(b) For all airplanes, revise the airplane Pilot's Operating Manual and Airplane Flight Manual (POM/AFM) by inserting Appendix 1 of this AD in the "LIMITATIONS" section of the POM/AFM. Appendix 1 procedures supersede any other POM/AFM procedures which may be contradictory.

(c) The requirements of paragraph (b) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(e) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, ACE-115W, 1800 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400 for MAI airplanes, or the Western Aircraft Certification Office, ANM-170W, 15000 Aviation Boulevard, Hawthorne, California 90261; Telephone (213) 297-1351 for MHI airplanes.

All persons affected by this directive may obtain copies of the documents referred to herein upon request to GTEC, P.O. Box 5217, Phoenix, Arizona 85010; Telephone (602) 231- 1000; Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201; Telephone (316) 681- 9111; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on December 31, 1986.

APPENDIX 1 - 86-26-02

Supplement to the POM/AFM, Mitsubishi MU-2B-10, -15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60

The CONTINUOUS IGNITION/MAN IGN switches shall be selected to ON during all operations in actual or potential icing conditions described herein:
(1) During takeoff and climb out in actual or potential icing conditions.
*(2) When ice is visible on, or shedding from propeller(s), spinner(s), or leading edge(s).
*(3) Before selecting ANTI-ICE, when ice has accumulated.
(4) Immediately, any time engine flameout occurs as a possible result of ice ingestion.
(5) During approach and landing while in or shortly following flight in actual or potential icing conditions.

*Note: If icing conditions are entered in flight without the engine anti-icing system having been selected, switch one ENGINE system to the ANTI-ICE ON position. If the engine runs satisfactorily, switch the second ENGINE system to the ANTI-ICE ON position and check that the second engine continues to run satisfactorily.

CAUTION

Flight in actual or potential icing conditions will be limited by duty cycle of the ignition system. Ignition system time limits must be observed to prevent exceeding duty cycle times. Operator should verify these limits for his particular installation. For the purpose of this supplement, the following definition applies:

"Potential icing conditions in precipitation or visible moisture meteorological conditions:
(1) Begin when the OAT is plus 5 degrees C (plus 41 degrees F) or colder, and
(2) End when the OAT is plus 10 degrees C (plus 50 degrees F) or warmer."

The procedures and conditions described in this appendix supersede any other POM/AFM procedures and conditions which may be contradictory.

FOOTER: