ENG FAIL L, R — After V1 (이륙 중 엔진 고장)

QRH: ENG FAIL L, R — After V1

한 줄 요약: V1 이후 엔진 고장 → 방향 조종 유지·VR rotate → 200 ft AGL safe altitude에서 "ENG FAIL (L)" 콜아웃 → Flap retraction 완료 후 QRH 7.16 실행. ENG FAIL 자체는 Memory Item 없음 (ENG FIRE일 때만 Memory Items 적용).

Trigger (POM 8.2.5, QRH 7.16)

V1 이후 엔진 속도가 idle 이하로 감속하여 추력 비대칭 발생 — EICAS: ENG FAIL L 또는 ENG FAIL R + adverse yaw + 다수 엔진 파라미터 이상.

[!IMPORTANT] 💡 RECOGNITION (POM 8.2.5) "Engine failure or loss of thrust is normally indicated by more than one engine parameter and adverse yaw. An instrument failure is normally isolated to the associated instrument and an electrical failure may affect instruments on more than one engine. Therefore, crew should use supporting information when verifying an engine failure or loss of thrust." → 단일 계기만 이상하면 instrument failure 가능성.

Memory Items (POM 8.2.5)

[!IMPORTANT] 💡 RULE (POM 8.2.5) ENG FAIL은 Memory Items 없음. Non-normal checklist는 flap retraction 후·condition 허용 시 수행.

ENG FIRE (severe damage/separation 포함) 시에만 Memory Items — "as soon as possible after 400 ft AGL".

ENG FIRE 병발 시 Memory Items는 아래 Reference Steps Section A-4 참조.

흐름 요약 (POM 8.2.5~7, QRH 7.16~7.20)

flowchart TD
    A[V1 이후 ENG FAIL 인지] --> B[PF 방향조종, PM ENGINE FAIL 콜아웃]
    B --> C[VR Rotate, 목표 pitch 11~12도]
    C --> D[Positive Climb, GEAR UP]
    D --> E{200 ft AGL safe altitude}
    E -->|도달| F[PM ENG FAIL L 콜아웃, PF A/P engage 가능]
    F --> G{400 ft AGL + 비행경로 안정}
    G -->|도달| H[Engine Out Accel Alt까지 V2~V2+15]
    H --> I[Accel Alt 도달, Flap Retraction]
    I --> J[CON thrust 확인, [QRH 7.16](source://QRH%207.16) ENG FAIL 실행]
    J --> K{Step 8 Abnormal vibration}
    K -->|Yes| L[Restart 금지, Step 20 single-engine ops]
    K -->|No| M{Step 9 Restart 필요}
    M -->|Yes| N[Step 10~17 Restart 절차]
    M -->|No| L
    N --> O{Start 성공}
    O -->|Normal| P[Checklist Complete]
    O -->|실패| Q[Step 18 CUTOFF, Step 22 nearest suitable airport]

Reference Steps (POM 8.2.5~7, QRH 7.16~7.20)

A. PF/PM Callout — ENGINE FIRE/FAIL AFTER V1 (POM 8.2.5~7)

원문 2열 callout 표 그대로 재현. 좌열=PF / 우열=PM.

1) V1 ~ Liftoff

[!NOTE] 💬 NOTE (POM 8.2.5) "Consider delaying 'ENGINE FIRE' or 'ENGINE FAIL' callout until landing gear is UP." — 기어 수납 완료 전까지 PM 콜아웃 지연 고려.

[!NOTE] 💬 NOTE (POM 8.2.5) AFDS는 V2+10 kts까지 bank angle을 **15°**로 제한 (maneuvering margin 확보). LNAV engaged 또는 HDG SEL/TRK SEL + bank limit AUTO 시 V2+20 kts에서 **25°**까지 증가.

2) Liftoff ~ 200 ft AGL

3) 200 ft AGL 이상 safe altitude 도달 시

[!IMPORTANT] 💡 RULE (POM 8.2.5) ENG FAIL: Memory Items 없음 → non-normal checklist는 flap retraction 후·조건 허용 시 수행. ENG FIRE (severe damage/separation 포함): Memory Items는 400 ft AGL 이후 가능한 빨리.

4) ENG FIRE 병발 시 Memory Items Callout (POM 8.2.6~7)

ENG FAIL 단독이면 이 섹션 skip. FIRE 병발 시에만 수행.

[!NOTE] 💬 NOTE (POM 8.2.6) "In case of FIRE ENG discharge the first bottle by memory. If after 30 seconds, the FIRE ENG message shows, PF should order a second bottle discharge by memory, ECL or QRH."

5) Engine Out Acceleration Altitude 이후

B. QRH 7.16 ENG FAIL L, R — 전체 절차

Flap retraction 완료 + AFTER TAKEOFF checklist 후 수행.

Condition: Engine speed is below idle. Objective: To restart the engine if needed, or configure for single engine operation.

Step 1~3 — 초기 판단 (QRH 7.16)

• Step 3: If an engine has separated → Go to ENG SVR DAMAGE/SEP L, R checklist (QRH 7.10).

Step 4~6 — Configuration (QRH 7.16)

• Step 4: A/T ARM switch (affected side) — Confirm — OFF
• Step 5: Thrust lever (affected side) — Confirm — Idle
• Step 6: FUEL CONTROL switch (affected side) — Confirm — CUTOFF

Step 7 — Checklist Suppression (QRH 7.17)

• Do not accomplish the following checklist: AUTOTHROTTLE

Step 8 — Restart 전제 (QRH 7.17)

[!IMPORTANT] 💡 RULE (QRH 7.17) "A restart can be attempted if there is no abnormal airframe vibration."

Step 9 — Restart 필요 여부 (QRH 7.17)

[!WARNING] ⚠️ GOTCHA — 판단 기준 QRH는 "needed/not needed"에 대한 수치 기준을 제시하지 않음. 유일한 명시 전제는 step 8의 "no abnormal airframe vibration". 실무 판단축:

• Vibration 존재 → restart 금지 (step 8)
• Engine severe damage/separation cue → step 3에서 이미 분기됨
• 원인 추정(fuel, ice, volcanic ash, transient surge) → 복구 가능성 있으면 시도
• 시도하려면 가능한 빨리 (FCTM 8.10: "high RPM 활용하려면 as soon as possible")
• 30,000 ft 이하가 windmill start 확률↑ (FCTM 8.10)

"저고도/착륙 임박이면 restart 말 것" → manual 규정 아님. 조종사 상황 판단 영역.

Step 10 — Slow Idle Acceleration Note (QRH 7.17)

[!NOTE] 💬 NOTE (QRH 7.17) "Engine can accelerate to idle very slowly, especially at high altitudes. If N2 is steadily increasing and EGT stays within limits, do not interrupt the start."

Step 11~12 — Crossbleed 분기 (QRH 7.17~7.18)

• Step 12: Autostart on → Step 13 / Autostart off → Step 15

Step 13 — Autostart ON 시 Abort 기준 (QRH 7.18)

[!CAUTION] 🚨 ABORT CRITERIA — Autostart ON "Do not interrupt autostart. Only abort the start if:

• There is no oil pressure indication after the EGT increases.
• EGT does not increase in 30 seconds.
• N2 is not increasing.
• No further autostart attempts are needed."

• Step 14: FUEL CONTROL switch (affected side) — RUN → Step 17

Step 15 — Autostart OFF 시 Abort 기준 (QRH 7.18)

[!CAUTION] 🚨 ABORT CRITERIA — Autostart OFF "Abort the start if:

• EGT does not rise within 30 seconds after selecting RUN.
• There is no oil pressure indication after EGT increases.
• N2 is not increasing.
• There is no N1 rotation indicated by 40% N2.
• EGT quickly nears or exceeds the start limit."

Step 16 — Crossbleed RUN 전환 (QRH 7.19)

Step 17 — Start 결과 (QRH 7.19)

Step 18~19 — Restart 실패 시 Cleanup (QRH 7.19)

• Step 18: FUEL CONTROL switch (affected side) — Confirm — CUTOFF
• Step 19: START/IGNITION selector (affected side) — NORM

Step 20~21 — Single-engine Configuration (QRH 7.19)

• Step 20: APU selector (if APU available) — START, then ON
• Step 21: Transponder mode selector — TA ONLY

Step 22 — Diversion 결정 (QRH 7.20)

[!CAUTION] 🚨 LIMITATION (QRH 7.20) "Plan to land at the nearest suitable airport."

Step 23~24 — Landing Flap 선택 (QRH 7.20)

[!NOTE] 💬 NOTE (QRH 7.20) Non-Normal Configuration Landing Distance 표는 ENG SHUTDOWN L, R in Performance Inflight-QRH 참조.

FCOM — System Background

ENG FAIL 시스템 설명(TAC, EEC, autostart 로직)은 추후 Systems/ 하위에 별도 정리 예정.

FCTM — Recommended Technique (FCTM 3.34~3.37, FCTM 8.10~8.11)

Engine Failure Recognition (FCTM 3.34)

"During an engine failure at or after V1, the TAC automatically inputs rudder to compensate for most of the yaw resulting from asymmetrical thrust. The PF is still required to add a small amount of rudder which aids in engine failure recognition. If the TAC is inoperative, the onset of the yaw may be rapid."

"The airplane heading is the best indicator of the correct rudder pedal input. To counter the thrust asymmetry due to an engine failure, stop the yaw with rudder. Flying with lateral control wheel displacement or with excessive aileron trim causes spoilers to be raised."

Rotation and Liftoff — One Engine Inoperative (FCTM 3.34)

• Target pitch: all-engine 대비 3~4° 낮게 → 결과 11~12°
• Rotation rate: normal 대비 0.5°/sec 느리게 → 결과 약 1.5~2.0°/sec
• Liftoff 후: V2~V2+15 유지되도록 pitch 조정
• Gear: positive rate of climb 확인 후 retract
• 엔진이 liftoff 이후 고장 시 TAC가 yaw 전체를 보상 시도. TAC inop 시 rudder+aileron으로 heading·wings level 유지 — correct rudder input은 control wheel을 대략 중앙에 두는 것.

Initial Climb — One Engine Inoperative (FCTM 3.37)

• V2~V2+15 유지, V2+15 초과 시 pitch 증가하여 V2+15로 수렴
• F/D roll mode: liftoff 후 LNAV 또는 다른 roll mode engage까지 ground track 유지
• 엔진 failure가 initial climb 중 발생 시: flaps retracted 후·조건 허용 시 checklist 수행

Autopilot Engagement (FCTM 3.37)

"When at a safe altitude above 200 feet AGL, with correct rudder pedal input as needed, the autopilot may be engaged. If the TAC is not operating, rudder trim must be manually applied."

Flap Retraction (FCTM 3.37)

• 최소 flap retraction 고도: 400 ft AGL
• 훈련 표준: 1,000 ft AFE
• Acceleration height는 recommended Flaps Up speed 가속 + 5분 내 (옵션 10분) MCT 설정 기준 계산

Restart 기법 (FCTM 8.10~8.11)

"There is a higher probability that a windmill start will succeed if the restart attempt is made as soon as possible (or immediately after recognizing an engine failure) to take advantage of high engine RPM. Establishing airspeeds above the crossbleed start envelope at altitudes below 30,000 feet improves the probability of a restart."

"A hung or stalled in-flight start is normally indicated by stagnant RPM and an increasing EGT. During start, engines may accelerate to idle slowly; no action is required if RPM is increasing and EGT is not near or rapidly approaching the limit."

Company Policy (POM 8.2.5~7)

POM은 Boeing 절차 위에 통합된 PF/PM callout 스크립트(ENGINE FIRE/FAIL AFTER V1)를 정의. 위 Reference Steps — Section A가 POM 원문 그대로.

Additional References (POM 8.2.7)

• FOM 8.2 — Engine Failure or Shutdown
• FCRM 7.6 — Non-normal Operations

Cross-References

• FFS RQ5 Lesson 5 — Engine Fire/Fail After V1 — 본 절차의 시뮬레이터 훈련 시나리오. Safe altitude(>200 ft AGL) + correct rudder → A/P engage 후 "ENG FAIL (L)" 콜아웃 시점 검증
• QRH Aborted Engine Start (지상 시동 중 abort) — ENG FAIL abort criteria(no EGT rise 30s, no oil pressure, N2 not increasing)와 로직 동일. 지상 abort와 공중 abort 기준 비교용