| AD Number | 51-19-04 | Status | Active |
| Effective Date | Not specified | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Martin-Marietta Corporation |
| Model(s) | 202 202A |
51-19-04 MARTIN: Applies to All Models 202 and 202A Airplanes Except as Noted.
Compliance required as specified.
In order to comply with the recommendations of the Martin 202 Modification Board, the following items must be accomplished. In all cases, modifications which are demonstrated to provide a level of safety equivalent to that provided by the modifications listed herein will be acceptable in lieu of the listed modifications.
A. Canceled December 22, 1952.
B. Compliance required by October 15, 1952.
1. Provide system independent of wing heat for windshield anti-icing, deicing defogging and birdproofing. Glenn L. Martin Service Bulletins Numbers 176 and 183 together with GLM Drawings Numbers 202A5051026, 202A5051027, 202A5051036, and 202A5051037 cover this same subject. (Applies to Model 202 airplanes only.)
C. Compliance required by January 1, 1952.
1. Redesign heater fuel control box to make leak tight and provide adequate draining.
2. Relocate emergency high seat switches to eliminate lag. (Applies to Model 202 airplanes only.)
3. Redesign fire-detection circuit to eliminate stepping relay. (Applies to Model 202 airplanes only.)
D. Compliance required by April 1, 1952.
1. Improve the landing gear position indicating system so as to reduce the possibility of obtaining a "safe" indication when gears is in an unsafe condition.
(Martin Service Bulletins Numbers 163A (for Model 202A) and 168 (for Model 202) cover this same subject.)
E. Compliance required prior to reactivation of the autopilot.
1. Accomplishment of the reduced gear ratio and installation of field rheostat in rudder servo motor circuit to reduce stall torque. Prototype installation to be approved by a Regional Office of FAA (Aircraft Engineering).
(Martin Service Bulletins Numbers 104A and 114 cover this same subject.) (Applies to Model 202 airplanes only.)
F. Compliance required before accumulation of 8,000 hours total operating time.
1. Accomplish reinforcement of the nacelle structure.
(Martin Service Bulletins Numbers 144 (for Model 202) and 145 (for Model 202A) cover this same subject.)
This supersedes AD 51-12-02.