F A I L S HID-TRAVEL ERRONEOUS INDICATION LOSS OF OR PARTIAL OUTPUT F A I L S T O OPEN/UOSE RESTRICTED FLOU SHORTED

¶ZMTERNAL/EXTERNAL LEAKAGE F A I L S T O START/STOP OPEN L E L E t T R I t A L )

¶FAILS OUT O F TOLERANCE F A I L S TO SWITCH LEAKAGE ( E t E r n I C A L )

Appendix 8. paragraph 3.1.1. sub-paragraph 13, r e f l e c t s the ground rule t o be used for external leakage. For OV-102 pre-AA mod only. those fa llure modes which result i n a criticality c la s s iflc a tion of 1 and 2, or 1R and a,and appear f n the CIL (Item 4.1.221 shall be c la s tlfle d further as structural or functional fal l ures by c l n l l n g 'S" or "F" I n the C32 fleld. The following guidelines apply: - STRUCTURAL (S) A fa ilure mode Involving structural fa ilure of a pressure vessel. ccrmponent housing, fluid lines, attach f i t t i n g s , or load-carryiag ambers such a s cranks or rods. FUNCTIONAL ( F ) - A fa llure mode, generally wlthln a canponent. which negates the described component function. Thfs type of fa ilure would Include bindlng. leakage, fa ilure t o open o r close. or loss of output. The f a i l u r e cause could be lmproper ins ta lla tion of parts o r structural fa ilure of power transmitting parts such as gear teeth, shafts or sprlngs; however. I n such . Instances t h e mode I s still c la s s lfie d as functional. Electrical and electronic component failures would nonnally f a l l I n t h i s category.

¶OI NO. 100-ZG

Page 1Jof 34 4.1.12 OV-102 PRE-AA MOO ONLY:

(C62-66) APPLICABLE MISSIONS: E n t e r an 'X' i n t h e block o f t h e mission t o which t h e FMEA a p p l i e s . Horizontal F l i g h t T e s t C62 Vertical F l f g h t T e s t C63 F e r y Flight C64 Operational F l i g h t s C65 '* S p e c i f i c O r b i t a l Mission C66 - Note: 'Operational F l i g h t s " and " S p e c i f i c O r b i t a l Mission" are not t o be used f o r t h e d u r a t i o n o f OV-101 and OV-102 f l i g h t test programs.

OPERATIONAL VEHICLE(SI: - (C83 C861 VEHICLE EFFECTIVITY: E n t e r an 'X' i n t h e appropriate b l o c k ( s ) t o which the FMEA appplies.

O r b i t e r Vehicle 102 C83 O r b i t e r Vehicle 099 C84 Orbiter Vehicle 103 C85 Orbiter Yehicle 104 & SUBS C86

¶4.1.13 (C33-37) MISSION PHASE(S1: Enter an "X" i n a p p r o p r i a t e box(es1 t o i n d i c a t e

when t h e s p e c i f i e d effects would be manifested. If t h e failure occurs a t d i s c r e t e p o i n t s i n time w i t h i n a given mission phase, and d i f f e r e n t e f f e c t s may be observed. i t may be necessary to d e f i n e t h e subphase or event under 'EFFECTS".

¶4.1.14 (C38. CS81 ABORT CRITICAL COMPONENTS:

a. For t h o s e items whose c r i t i c a l i t y i s increased t o 1/1 during an a b o r t r e s u l t i n g from unrelated f a i l u r e s . e n t e r t h e word "Abort" (C38 s i x - spaces o n l y ) , followed by t h e a p p r o p r i a t e acronym(s); i .e., - (CS8) RTLS Return t o Landing S i t e (C58) g - Abort Once Around (C.58) ATO - Abort t o O r b i t b. F o r non-redundant modes where normal mission e f f e c t i s c r i t i c a l i t y 3 b u t a r e hardware c r i t i c a l i t y 1 unique t o I n t a c t abort. c l a s s i f y t h e s e modes

¶0246j/l3

340

DI NO. 100-26 -. Page 1 4of 94 as hardware c r i t i c a l i t y 1 and functional c r i t i c a l i t y 1. Add i n J10 (FUNCTION) the notation, "Unique t o Intact Abort'. Add'appropriate Intact abort notation In a. above. Additional Information must also be entered under 5240, EFFECT(S) see - paragraph 4.1.16. E: For SSME induced aborts, maximum two engine burn time I s approximately twelve minutes. If "TIME TO EFFECT" Is equal t o or

¶- greater than twelve m i n u t e s , there i s no change i n c r i t i c a l l t y .

¶4.1.15 (5380) CAUSE/S): Enter causes Including but not limited t o those l l s t e d

below and amplify a s necessary. See paragraph 4.4.2 f o r instructions on supplier furnished piece parts.