Ex-Navy pilot loses libel suit, again

Just dont fall asleep on the Dog. You will regret it.

The fleas were like pepper

No! I won't go back to the Anthony Wayne Hotel in Waynesboro, PA.
EOD, you're right, gotta watch dem sailor folk.

I always sleep on my back with a pillow over my head.

When and where, man?

Give me 6 months, I starting my Delta training in 4 days.

Just dont fall asleep on the Dog. You will regret it.

I get it, Stay up late, wake up early or pay the price...

Naval Aviation ping.

I always sleep on my back with a pillow over my head.

There are many place where one can find a pillow that feels just like a hairy ass.

Give me 6 months, I starting my Delta training in 4 days.

Deal!

This ruling closes a part of this op-ed piece by Walter E. Williams (on of my favorite writers) from April, 1997. Go to the 2nd paragraph.

Gender-Norming Update
by Walter Williams (April 4, 1997)

www.CapitalismMagazine.com] In October 1994, Lt. Kara Hultgreen was killed during an attempted landing of her F-14 on the aircraft carrier Abraham Lincoln. Femfeared (fear of feminists) Navy officials first re ported that engine failure caused the death of the Navy's first female F-14 pilot. That was a deliberate lie and coverup as later revealed in a leaked Mishap Investigation Report and the Navy's Judge Advocate General's report. After three requests, under the Freedom of Information Act, the Center for Military Readiness recently obtained a 1995 report written by Admiral Lyle G. Bien. The report confirms special treatment for female F-14 pilots. It also confirms that Lt. Hultgren was retained in the F-14 training program and graduated to the fleet despite low scores and four major errors (Downs), two of which were similar to those made the day she died. Just one or two major Downs have been enough to send men packing.

Then there's Lt. Carey Lohrenz, who was washed out of the F-14 program, who's brought suit against Elaine Donnelly, Director of the Center for Military Readiness and several newspapers. Lt. Lohrenz claims public release of her training records violated her privacy. Claiming sex discrimination, she's demanding reinstatement. Her training records are reported as being "the lowest night grades in the history of the FRS [Pacific F-14 Fleet Replacement Squadron] . . . no pilot in the history of the FRS was allowed to attempt requalification with grades as low as hers."

Aircraft carrier maneuvers are error unforgiving. Pilot incompetency not only jeopardizes the life of the pilot but crew members and the ship's mission as well. Case in point: during refueling, Lt. Lohrenz failed to secure the F-14's right engine so as not to suck approaching crew members into a turning engine. Since there is so much noise on deck, crew members can't tell whether an engine is off; it's the pilot's responsibility. Because of the alertness of the flight instructor a catastrophe was averted. Lt. Lohrenz was given the minor demerit, Signal of Difficulty (SOD), instead of a more serious Down. Other concessions included no Downs for serious violations such as not engaging automatic maneuvering devices in air combat maneuvering engagements. Officers who insist that females be held accountable to the same high standards as males are seen by higher brass as obstructionist and risk their careers.

Double standards to accommodate women have compromised military effectiveness. Women are three to four times as non-deployable as men as we learned during Desert Storm. Despite relentless sex education and condom distribution, pregnancy rates average 8 to 10 percent, and are much higher in some enlisted units. Fighting ships compromise their missions to insure the safety of pregnant females. Training standards have been lowered to accommodate lower strength and stamina of women.

The General Office of Accounting (GAO) reports that annual surveys done at service academies since 1992 show that complaints about double standards have been identified as the first or second most common form of verbal sexual harassment. Male resentment against double standards is sometimes expressed in inappropriate ways that have been featured in recent news stories of sexual, harassment, intimidation and rape at military posts.

There are physical differences between the sexes that affect combat readiness, but those differences do not deny a role for women in the nation's defense. Women were indispensable and served honorably in WWII. The femfeared military leadership does not have the guts to recognize sex differences and are willing to risk national security to appease radical feminists.

About the Author: Born in Philadelphia in 1936, Walter E. Williams holds a bachelor's degree in economics from California State University (1965) and a master's degree (1967) and doctorate (1972) in economics from the University of California at Los Angeles.

Navy officials first re ported that engine failure caused the death of the Navy's first female F-14 pilot. That was a deliberate lie and coverup as later revealed in a leaked Mishap Investigation Report

Leaked, huh? Hell, who wants to see it?

I guess that explains how the back seat guy got out when the aircraft started to roll. I would suspect that anyone who had to fly with her, flew with both hands on the ejection seat D-ring just in case.

I saw the video of the landing, I wish I had a copy. I was working a job for the engine mfg at the time, and they were analyzing the tape and going berserk because the stall of an engine should not have made the plane roll as it did. and the rudder looked like it moved. At that slow speed of approach, she probably stalled the left wing, causing the roll.

The GIB ejected at about +30 to +20 deg. to horizon, Pilot then was ejected at about -20 to -30 deg. to the horizon and was rocketed into the ocean, likely killed on impact with the ocean.

Have you ever seen the report?

Not only have I seen it, I have it.

At low speed I think a rudder can also start a roll and in combination with then stalling the left wing, she was done.

AND

Kara forgot that at high Alpha, rudder will roll the Tomcat; combined with mil power on the starboard engine, she pushed the nose right at the water.

Is that the wrong report saying the engine fault was the root cause or the corrected report with pilot F/U?

F-14A Mishap Investigation Report

(Military City Online note: This is the Mishap Investigation Report into the
Oct. 25, 1994, crash that killed a Navy F- 14A Tomcat fighter pilot, Lt. Kara
Hultgreen. The report, which was released only to a limited number of
members of the aviation community, includes a list of acronyms used in the
text.)

1. Summary: Aircraft impacted water during day CV landing approach. Aircraft
destroyed.
2. Data.
A. Aircraft. (1) F-14A, (2) 160390, (3) 103, (4) VF-213.
B. Equipment. (1) drop tank (two), (2) Grumman, (3) A5lP7100-27, (4) AFWA.
C. Environment. (1) 25 Oct 94, (2) 1501, (3) t, (4) day,
(5) 32 04.2N/117 27.2W, NZY 190 Radial/41 DME, off coast of San Diego, Ca.
(6) sea level, (7) 20 ovc 10, wind 310/15, altimeter 30.01.
3. Circumstances.
A. Origin. NAS Miramar
B. Mission. CQ refresher
C. FLT purpose code. 1A4.
D. Type of flight plan. IFR, VMC.
E. Destination. USS Abraham Lincoln (CVN-72).
F. Aircraft evolution. CV landing.
4. Mishap category. Class a flight mishap, aircraft destroyed.
5. Damage and costs.
A. Aircraft.
1. F-14A, 160390, destroyed.
B. DoD property damage. Two drop tanks, $111,900.

C. Non DoD property damage. none.
6. Personnel information, injuries and costs.
A. Souls on board. two.
B. Crew. Pilot at controls, LT, 1310, USN, VF-213, on duty, fatal injury,
NVGS not used, 1241.9 total hrs, 217.9 F- 14A hrs- RIO, LT 1320, USN VF-213,
on duty, first aid injury, NVGS not used, 697.7 total hrs, 477.1 F-14A hrs.
C. Total number of passengers. None.
D. Injured non-occupants. None.
7. Mishap investigation. AMB investigation complete.
8. JAG manual investigation. This mishap does meet the requirements in ref b
for a JAG manual investigation. JAG investigation complete 14 feb 95.
9. Point of contact.
A. Aircraft mishap board.
- Senior member: Cmdr. S.E. Luce, USN, VS-29, DSN: 7350820, COMM: (619)
545-0820
- Aircraft maintenance: Lt N.P. Jennings, USN, VF-213
- Aircraft operations: Lt.Cmdr. J.S. Bates, USN, VF-213
- Aviation safety: Lt. M.B. Whetstone, USN, VF-213
- Aviation Safety: Lt J.A. Tekverk, USN, VS-29
- flight surgeon: Lt S.M. Miller, USN, CVW-11, DSN: 577 4669, COMM: (619)
537-4669
B. Telephone inquiries. VF-213: DSN: 577-4526, COMM: (619) 537-4526
10. Evidence.
A. Enclosures [[REMOVED]]
B. Summary of Evidence.
(1) The following acronyms are used in this msg: [[REMOVED]]
WUOSX - wrapped up overshooting start

(2) Definitions [[REMOVED]]
(3) Aircrew data
(A) MP was first operational tour naval aviator with 1241.9 total FLT hrs
including 217.9 F-14A flt hrs. MP had total of 58 carrier landings: 48 F-14A
carrier landings (31 day and 17 night). MP assigned to MS 30 Aug 94. Primary
billet assignment was public affairs officer. (3a,4a)
(B) MP had flown 25.4 hrs in last 30 days, and 8.5 hrs in last 7 days. Last
carrier landing was 30 Aug 94. last
FLT prior to MF was 24 Oct 94. (3A)
(C) MR was a first operational-tour naval flight officer with 697.7 total FLT
hrs including 477.1 F-14A FLT hrs. MR had a total of 150 carrier landings
(80 day and 70 night) all in F-14A. MR assigned to MS 04 Jan 93. Primary
billet assignment was assistant line division officer. (3A,4A)
(D) MR had flown 20.7 hrs during last 30 days, and 6.7 hrs in last 7 days.
last carrier landing was 24 Aug 94. Last FLT prior to MF was 24 Oct 94.
(3A)
(E) (P) MP last documented act was 17 may 90. However, interviews confirm MP
completed act during FRS syllabus. FRS act is not documented. (5A)
(F) MR completed annual act in MS Mar 94. (5A)
(G) MP and MR were crewed 12 Oct 94, and flew
ight sorties together prior to MF, completing 9.4 FLT hrs, 2.3 day/7.1
night. MC had no CV landings as a crew. MP and MR last FLT together prior
to MF was a 1.1 hr FCLP flight, 24 Oct 94. (3A)
(H) MP and MR were fully qualified for MF iaw all applicable directives. (5A)
(I) MF was authorized by the MS commanding officer per ref D. (6A)
(4) LSO data
(A) CLSO was wing and training qualified CVW staff LSO (A-6 background); wing
qualified Jan 91, training qualified Oct 91. (7a)
(B) BLSO was wing, training, and staff qualified CVW staff LSO (E-2
background); wing qualified Jul 91, training qualified Aug 92. (7A)
(C) (P) BLSO was familiar with MP's landing performance. (5b)
(D) MS LSO structure consisted of one experienced wing qualified LSO.
(5) Aircraft data
(A) MA had flown six sorties/7.3 FLT hrs in previous seven days and 28
sorties/41.5 FLT hrs in previous 30 days.
(B) MA maintenance record audit found the following pertinent maintenance
actions entered and outstanding at time of MF: (1) discrepancy: R/C A/S
three knots slower than F/C A/S and computed landing A/S at optimum (on
speed) AOA.
(2) Discrepancy: left engine AB takes five sec to stage. Right engine
operates
normally.
(3) Discrepancy: throttles go to manual upon deselecting AB.
(C) (P) MA basic weight was 44,700 pounds. F-14A NATOPS (ref C) maximum CV
landing weight is 54,000 pounds. MR testimony states fuel weight was
9,000
pounds at time of mishap; MA total approach weight was 53,700 pounds.
(3B)
(d) F-14A NATOPS (ref C), Fig 11-9
indicates approach speed for a 53,700 pound F-14A with modified DLC in
the
neutral position (engaged) is 139 KIAS.
(6) Aeromedical data
(A) MP and MR had current FLT physicals and valid aeromedical clearance
notices. (5A)
(B) (P) MC had unremarkable 72 hour histories with adequate rest preceding
MF.
MP had approximately 7.5 hrs of sleep the night prior to the MF. MP
awakened at 0700. At time of mishap MP had a 3.5 hour duty day. (2B)
(C) (P) MR was located floating approximately 200 yards off ship's port
quarter. MR rescue by SH-60 occurred four minutes 29 seconds after
ejection. MR transported to CV medical department for observation. MR's
injuries detailed in AA. (8A, 17A, 2B)
(D) MP recovered from ocean bottom 19 days after mishap. MP still attached to
ejection seat by lap belts. MP's injuries detailed in AA.
(7) Aviators life support system data.
(A) MP FLT gear was recovered with MP and ejection seat after 19 days
immersion in salt water. FLT gear was intact, and MP was attached to
ejection seat by lap belts. Seawars activated
properly. MP ALSS inspection revealed LPU inflation occurred
automatically. MP upper right lobe of LPU did not inflate.
(B) MP helmet and portion of mask recovered after mishap. Minor impact
damage
to MP helmet; left oxygen mask bayonet receiver upper cover plate
missing;
center oxygen mask, and MIC assembly and hose separated from mask. Right
bayonet fitting/attachment remained intact.
(C) (P) MR statements reveal right seawars failed to actuate on water entry.
MR manually released right upper koch fitting. Safety center data
indicate
10 of 73 seawars failed from 1980 to 1994 in F-14A community. (3B)
(D) (P) MR retained helmet/mask during ejection. Inspection revealed no
pertinent discrepancies. (3B, 9B, 20B)
(E) (P) MP ejection seat recovered. EI revealed
the following: all explosives, except the guillotine cartridge,
functioned properly. Harness reel straps fully retracted and released via
the time release mechanism. Water impact damage interrupted the normal
mechanism and prevented survival kit lugs and leg restraint locks from
releasing. Leg restraint lines subsequently released by outward
distortion
of seat bucket sides upon water impact. (9A, 23A, 12B)
(F) MR ejection seat recovered. seat functioned properly. EI not required.
(G) (P) MR has excellent recall of ejection sequence, including activation
utilizing lower ejection handle, canopy separation, seat/man separation
and water entry. (3b)
(8) Chronology
(A) (P) All times local. times from 0700 to 1457 are approximate. (17A, 2B,
3B, 4B, 5B, 9B) 07:00 - MP awakes.07:30 -
MR awakes.
11:45 - MR arrives at squadron.
12:15 - MC begin brief for FLT.
13:05 - MC proceeds to review ADB/preflight MA.
14:00 - MA takes off.
14:34 - MA established in marshall with 16,000 pounds fuel.
14:44 - MP dumps fuel to 12,800 pounds total remaining.
14:54 - MA commences approach from marshall.
14:57 - MP dumps fuel to approx 10,000 pounds.
15:00:15 - A/C 116 (flight lead) FD WO.
15:01:01 - MP arrived at ninety, 450' MSL, 145-148 kts, 100 FPM rod.
15:01:03 - MP responded to MR ICS ``you're five kts fast'' with ``roger.''
15:01:05 - MR, ``103 tomcat ball, Hultgreen.''
15:01:06 - MA crosses wake of ship. MR hears almost imperceptible ``pop''
from
MA. MR ICS, ``you're on speed.''
15:01:07 - CLSO, ``roger ball.''
15:01:10 - MA crosses (overshoots) extended landing area centerline. MR, ICS,
``we're 10 knots slow, let's get some power on the jet.''
15:01:11 - MA wings level. black smoke trail from ma right eng only.
15:01:13 - Black smoke trail from ma starts to fade.
15:01:14 - BLSO, ``waveoff,'' and activates wave-off lights.
15:01:14 - CLSO transmits, ``waveoff, waveoff.'' cutting out BLSO's ``level
your
wings and climb'' call. 15:01:16 - bLSO, ``waveoff,'' MA crosses
extended landing area centerline from MA right to left. Black smoke
trail from MA disappears. 15:01:17 - BLSO, ``power.''
15:01:18 - BLSO, ``raise your gear.''
15:01:19 - BLSO, ``raise your gear.''
15:01:20 - BLSO, ``power.''
15:01:20 - MA, from wings level, begins approx 90 deg/sec left roll.
15:01:21 - CLSO, ``eject, eject.'' MA approx 50 deg left wing down and 10 deg
nose down as ejection is initiated. MR ejection occurs at approx 90
deg left AOB, still 10 deg nose down.
15:01:22 - MP ejection occurs when MA approx 110 deg left AOB, approx 25 deg
nose down.
15:01:23 - MA impacts water approx 70 deg nose down and approx 165 deg left
AOB. MR separates from ejection seat.
15:01:24 - MR chute fully deployed.
15:01:25 - Air boss, ``where is the plane guard?''
15:01:26 - Plane guard, ``inbound.''
15:01:27 - MR enters water.
15:01:29 - CLSO, ``99 delta.''
15:03:18 - First helo on top MR.
15:05:43 - Second helo on top MA.
15:05:52 - Rescue swimmer and MR out of water.//

(A) MP designated naval aviator Aug 1989. MP reported to VA 42, east coast
A-6 FRS Jan 90. MP served in VAQ 33 from Apr 90 to May 93 accumulating over
700 hrs in the A-6E and EA-6. MP reported to west coast F-14 FRS,
VF-124, 22 Jun 93. FRS performance ranking by phase was: 2 of 5 FAM, 3 of 5
BWEPS, 4 of 5 CW/GUNS, 2 of 5 tactics, 1 of 5 ADFAS, 1 of 5 air refuel, and 3
of 7 CQ. MP disqualified during initial CQ, Apr 94. MP successfully
completed CQ phase in Jul 94. MP completed VF-124 with number 3 of 5 class
ranking. (5a, 10a, 11a)
(B) MP performed over 170 FCLP approaches in preparation for first CQ
attempt. FCLP GPA was 2.82. although INC, MP disqualified for night GPA and
boarding rate during initial FRS CQ attempt in Apr 94. MP ranked 8 of 9 with
GPA/boarding rate as follows: day 2.79/79 percent, night 2.32(inc)/64
percent, overall 2.62/73 percent. AIRPAC CQ GPA/boarding rate qualification
minima ARE 2.60/60 percent in each phase: day/night/overall. (11a)
(C) (P) MP's first FRS CQ RIO instructor stated MP was highly motivated
during CQ phase and remained positive following DQ. Evaluation of MP by FRS
CQ phase leader showed well below average field performance, slightly below
average day CV performance, and unsatisfactory CV night performance. First
CQ (day) trends reveal sporadic glideslope deviations due to untimely power
corrections, and angling starts (11a, 7b, 8b)
(D) (p) From Jun 92 to Sep 94, 69 pilots attempted CQ at VF-124.
qualification results as follows: 51 pilots qualified during initial
attempt, 17 pilots disqualified first attempt and qualified second attempt,
one pilot required third attempt to qualify. First attempt DQ rate is
approximately 25 percent. each pilot successfully completed FRS syllabus.
East coast FRS percentages are nearly identical.
(E) MP flew more than 170 FCLP approaches during preparation for second FRS
CQ attempt. FCLP GPA was 3.24. MP qualified during second FRS CQ attempt in
Jul 94. MP ranked 3 of 7 with GPA/boarding rate as follows: day 3.22/89
percent, night 2.82/71 percent, overall 3.05/81 percent. (11a)
(F) (P) qualifying FRS RIO instructor stated MP was safe and consistent.
evaluation of MP by FRS CQ phase leader showed average field performance,
above average CV day performance, average CV night performance, and slightly
above average overall CQ phase performance. Second CQ (day) trends reveal
Solid pattern work, and overpowered starts with timely corrections. (11a,
7b, 8b) (G) MP last documented act was 17 May 90 in VAQ-33. (5a)
(H)(P) MP attended annual act at FRS, which was documented. (5a)
(I) MR attended annual act training Mar 94 at MS.
(5a)
(J) F-14A aircrew act consists of standard syllabus developed by interscience
America and includes comprehensive lessons on: message/ feedback, importance
of communication, situations requiring adaptability/flexibility, etc.
(K) (P) MP performed three practice emergency FCLP flights during four months
prior to MF, two during FRS training, and one in MS prior to previous at-sea
period. Each flight included two simulated single engine approaches.
(L) (P) FRS syllabus includes SSE waveoff practice during FCLP's. Records
were unavailable to confirm MP received SSE waveoff practice in FRS.
additionally, interviews and records indicate MP performed no SSE waveoff
practice while attached to MS.
(M) (P) Interviews with naval safety school revealed no history of F-14A eng
comp stall in landing pattern.

(N) MP completed TSTA III (25-30 Aug 94) aboard USS Abraham Lincoln (CVN-72)
while TAD to MS from FRS. MP performed 12 carrier approaches; seven day and
five night. First six landings were day/night CQ: four day passes were case
III straight-in approaches, two touch and go's, two traps; and last two were
night traps. CQ GPA/boarding rate was 3.00/100 percent. MP flew six TSTA
III operational paSSEs, four day/two night for a GPA/boarding rate of
3.17/100 percent. Three day passes were case I pattern. Performance on the
six post-CQ landings placed MP in approx top half of all air wing pilots. MP
was top MS nugget for the line period 28 Aug to 25 Oct 94. (11a,- 13a, 21a)
(O) MP completed CVW-11 Fallon detachment 07 Oct 94 and subsequently
completed eight FCLP periods in preparation for COMPTUEX 95-1A which began 25
Oct 94. MP received favorable comments from MS LSO concerning FCLP periods.
Additionally, MP completed two simulators and four CQ/LSO training lectures.
During one simulator, MP flew one single engine approach. No SSE waveoff
practice was performed. Lecture topics included MOVLAS, CV OPS, phraseology,
and CQ procedures. (11a) (P) MR had 464.4 F-14A flt hrs as of 30 Sep 94.
Nine MS RIO's had more F- 14 flight time than MR. (22a)
(Q) (P) MR was cruise experienced and had the trust and confidence of the
command. MR earned NATOPS instructor and PMCF RIO quals and was regularly
scheduled to fly with vip/guest pilots. (5a)
(R) (p) MS COo and OPS officer considered MC a competent crew pairing. MS
COo and OPS officer were confident in MP's CQ ability.
(S) MC began flying together 12 oct 94. MC had a total of 8 sorties/9.4 flt
hrs as a crew prior to mf. All sorties were FCLP missions at nkx and nuc.
(3a)
(T) (P) MC received complete and thorough CQ brief and section brief, and
briefed as a crew prior to MF. MC briefed single eng during catapult launch,
and low altitude ejection procedures. (3b, 9b)
(U) (P) MA had proper daily and turnaround inspections and was configured for
CV landings. MA had no downing discrepancies and was properly released safe
for flight. (20a, 10b)
(V) R/C A/S discrepancy of three kts slow at on speed was within acceptable
limits IAW MS sop. (12a)
(W) (P) Left eng AB time to stage, though slow at five seconds, was within
acceptable limits for flight.
(X) (P) MC was wingman in two-plane formation entering CV landing pattern for
case IIi recovery. (9b)
(Y) (P) MP performed normal CV break at approx three NM upwind. MC
recognized wide abeam position on downwind leg and made correction arriving
slightly close abeam at 1.0 NM, approx 570 ft MSL. (3b)
(Z) (P) MA was noted slightly close abeam by BLSO.
(5b)
(AA) (P) MR had avia selected on TID. (3b)
(AB) (P) MA extended slightly past abeam to correct for close abeam. (3b)
(AC) (P) MA flew approx 10 kts above computed on speed during initial portion
of approach turn.
(3b)
(AD) (P) MA flew approx 100 FPM rod until ninety. (3b)
(AE) (P) MC had ICS cold MIC selected during approach. (3b)
(AF) (P) MA arrived at ninety approx 450 ft MSL, 145-148 kias. (3b)

(AG) (P) Two seconds later MR ICS comm ``you're five knots fast'' was
acknowledged by MP with ``Roger.'' MP did not TXMT on ICS throughout the
remainder of MF. (3b)
(AH) MS SOP states, ``aircrew will acknowledge all ICS calls from the other
cockpit.'' (12a)
(AI) (P) MA maintained approx 100 FPM rod until forty-five. (3b)
(AJ) (P) MA approach appeared normal through forty five. (3b, 4b, 5b)
(AK) (P) Witness statements confirm MA was in proper configuration for
arrested CV landing. (3b, 4b, 5b)
(AL) (P) As MA crossed ship's wake, MR noted MA five kts fast. During
post-mishap recollection MR recalled hearing an almost imperceptible ``pop'',
described as ``popcorn stall''type of sound. (3b)
(AM) (P) MA flew WUOSX, 42 to 45 DEG AOB. (13a, 17a, 4b, 5b)
(AN) (P) CLSO and BLSO observed excessive left YAW on MA; attributed to
perceived use of rudder to avoid overshoot. (4b, 5b) (AO) (P) MA rolled out
wings level at start, on speed, 325 feet agl, with 400 FPM rod and on
glideslope. (3b)
(AP) (P) MR scanned centered ball, then noticed MA five knots slow; looked
outside again, then noticed MA ten knots slow. (3b)
(AQ) (P) MR advised mp ``we're ten kts slow, let's get some power on the
jet.'' MP did not verbally acknowledge, but MP added power. (3b) (AR) (P) MR
states aircraft started to YAW left. (3b)
(AS) (P) MA waved off by BLSO for WUOSX with left YAW. ``Waveoff'' was
echoed by CLSO cutting out BLSO's ``level your wings and climb.'' BLSO
subsequently transmitted ``power, raise your gear, raise your gear, power.''
``burner'' call was not used by LSO. ``Burner'' is a standard imperative LSO
phrase. (17a, 4b, 5b)
(AT) (P) AB plume was visible from MA right engine only. (9b, 13b)
(AU) (P) MR did not recall hearing ``raise your gear'' calls. MR heard only
``waveoff'' and ``power'' comm from LSO's and does not recall any subsequent
LSO comm. (3b)
(AV) (P) U.S. Navy LSO school, ILARTS analysis states, ``...just after the
start position the LSO (BLSO) felt the approach was not within standards and
tried to remedy the situation with an early waveoff call.'' Additionally,
analysis states, ``All calls ... were timely and necessary.'' (11b)
(AW) F-14A NATOPS manual (ref c), chapter 15 landing emergencies, page
v-15-1, single engine landing, states: ``single-engine landing, bolter, or
waveoff may be accomplished safely up to the gross weight limits for
two-engine operation. ``during waveoffs or bolters, select mil thrust, rotate
not to exceed 14 units AOA as for normal two engine takeoff ... ; page
v-15-2, ``warning extreme caution must be exercised when performing turns
into a dead engine. Decaying Airspeed/increasing AOA can rapidly result in a
situation where there is not enough rudder authority to return the aircraft
to level flight, and insufficient altitude to effect a recovery ``warning -
military power climb performance during heavy waveoffs may not adequately
arrest high sink rate conditions. Use of full AB provides a significant
increase in climb performance. Up to full rudder may be required to counter
AB asymmetric thrust yawing moment during waveoff or bolter. Do not exceed
14 units aoa during waveoff or bolter.''
(AX) F-14A NATOPS manual, page IV-11-23, asymmetric thrust flight
characteristICS, landing configuration, states: ``steep angle of bank turns,
particularly into the dead engine, reduce climb performance and may result in
rudder requirements exceeding available control deflection causing loss of
control.'';
And, ``if AB is used, the pilot should be prepared to use up to full rudder
to counter the large YAW moment produced. Late rudder application that
allows sideslip buildup may result in loss of aircraft control even with full
rudder. Lateral stick should not be used alone to counter yawing moment.
However, if lateral stick is used, it should be applied coincidental with or
after rudder inputs. A maximum of 14 units AOA should be used on all
waveoffs since rotation to higher AOA does not significantly reduce sink
rates...''
(AY) (P) BLSO noticed MA nose slowly rotating up as if mp was attempting to
arrest rate of descent with nose attitude vice power. (5b)
(AZ) (P) MA right spoilers were fully deflected up, left spoilers were flush.
(9b)
(BA) (P) recording LSO observed MA rudders deflected full right during final
seven seconds prior to water impact. (6b)
(BB) F-14A NATOPS manual, page 1-2-119, states ``landing gear retraction
takes nominally 9-15 seconds.''
(BC) (P) There is no evidence to indicate MP attempted to retract MA landing
gear. (17a, 2b)
(BD) (P) Mr felt MA was under control and was going to successfully fly away.
(3b)
(BE) (P) simulator tests duplicating MF reveal that MA was controllable up to
20 units AOA. Above 20 units AOA, aircraft was uncontrollable and departed
controlled flight with rapid left roll off. (13b)
(BF) (P) MA rapidly rolled left wing down. (17a, 3b, 13b)
(BG F-14A NATOPS manual (ref c), chapter 16 ejection and bailout, p. v-16-1
states ``responsibility for the decision to eject shall be determined and
briefed prior to flight. Thereafter the decision to abandon
The aircraft shall rest with the crewmember assigned responsibility for that
particular situation.'' Additionally, REF C states ``in each case, the pilot
must decide when to eject...''
(BH) (P) during final seconds of MF, MR was externally evaluating ejection
criteria relative to CV flight deck elevation. If MA descended below flight
deck level, MR was going to eject MC. (3b)
(BI) (P) MC flew with eject command lever in command mode allowing MP or MR
to eject both crew. (3b)
(BJ) F-14A NATOPS manual, pg 1-2-157, states that ``command ejection by
either crewmember will eject the rio first and the pilot 0.4 seconds later.
Total time for ejection is 0.9 seconds.'' F-14A NATOPS manual, pg 1-2-156,
states ``ejection trajectories are canted laterally to provide additional
separation of the seats. The RIO is ejected to the right and the pilot to
the left.''
(BK) (P) MR initiated ejection upon commencement of MA left roll. (3b)
(BL) (P) MA canopy jettisoned with MA at approx 50
deg aob. (17a)
(BM) (P) MR rocket motor initiated with MA approx 90 deg AOB/10 deg nose
down, approx 65 ft MSL. (17a)
(BN) (P) MR safely ejected and achieved normal parachute deceleration,
entering water approx 300 yards off CV port aft quarter.
(BO) (P) MP rocket motor initiated with MA approx 110 deg AOB/25 deg nose
down, approx 55 ft MSL. MP rocket motor burn completed with MA approx 135
deg AOB/35 deg nose down. (17a)
(BP) (P) MP did not achieve seat-man separation prior to water impact.
(BQ) (P) Water impact damage interrupted normal MP ejection seat operation.
Water impact speed estimated at 235 ft/sec. (9a, 12b)
(BR) (P) MA impacted water at approx 165 deg left aob, 70 deg nose down. MA
came to rest upright approx 120 deg clockwise from initial approach heading.
(17a)
(BS) During MA final approach CV was maintaining 15 kts and turning slightly
left from 333 to 330 deg true hdg. (8a)
(BT) (P) Flt deck winds were down the angle at 2527 kts. (4b)
(BU) Weather at time of mishap: estimated 2000 ft overcast, visibility 10 sm,
wind 310/15 kts, altimeter 30.01, outside air temperature 65 deg f, sea state
1. (18a)
(BV) (P) MR and MP had good ICS and UHF comm during entire flt. (3b)
(BW) In the tf30 engine the smallest stall margin exists for stages 4-9 of
the N-1 (low pressure) compressor. (14a)
(BX) F-14A NATOPS (ref c), pg I-2-16 states: MCB bleed air is ported from the
seventh stage of the low pressure compressor into the fan bypass duct during
certain flight parameters in order to increase eng comp stall margin.
(BY) (P) MCB test lights are located on the MCB Test panel in the R/C.
Illumination of the lights indicates only that the electrical circuits are
operating, but does not verify MCB operation. MCB test panel normally in off
position except during PMCF.
(BZ) Left eng MCB system was stuck in the bleeds closed position prior to
impact, preventing seventh stage bleed air from being ported into the fan
bypass. This condition was caused by a failed directional control linear
bleed control valve (solenoid) assembly. Particularly, disassembly of the
directional control linear bleed valve assembly revealed the pin was stuck in
the spacer stop, the plunger was stuck in the solenoid, and the solenoid
valve was stuck in the liner. The pin, spacer stop, solenoid valve and top
of the plunger (it remained stuck in the solenoid) were found to be caked
with a dark powder like debris. The debris Examined was consistent with wear
generated particles of the components' nickel plating and wear generated
particles of the parent metals. There was no evidence of contamination of
the assembly by lubricants. (14a)
(CA) (P) Full operation of MA left engine was last checked during test trim
run at hot section inspection/change, 601 operating hrs prior to MF. MCB
system was operating properly at that time.
(CB) (P) MCB system had been stuck in bleeds closed position an undetermined
period of time.
(CC) (P) discussion with NADEP engineers reveals that eng stall margin
increase gained with MCB system open vice closed varies from 23 per cent at
idle to 26 per cent at mid power (8283 per cent) to 18 per cent at military
power although stall margin remains marginal (14b).
(CD) TF30-P-414A eng stall margin may be checked on Preinduction or
troubleshooting test cell runs. (14a)
(CE) (P) F-14A TF-30 engine hot sections are changed no later than 750 hrs of
operation. Only 25 per cent of Tf-30 engine hot sections remain in service
beyond 600 hours of operation. They are removed for various reasons: fod,
turbine failure, high oil consumption, etc. Information is based on two and
one half years data ended summer 1994 at NADEP Norfolk, Va and contains
approx 400 data points.
(CF) F-14A NATOPS (REF C), pg IV-11-4, para 11.4.2.1 states ``The engines
generally operate satisfactorily at extremely high positive or negative AOA
but are prone to compressor stalls if high AOA is combined with sideslip ...
or throttle settings below 90 percent RPM.... Each of these conditions
reduces the engine's compressor stall margin, which is already reduced when
operating at high AOA. Excessive sideslip, even at low AOA, may result in
compressor stalls anywhere in the aircraft flight envelope.''...``There is no
way to predict when a compressor stall will
Occur, but there is a likelihood of inducing one by changing throttle
settings at high AOA.'
(CG) F-14A NATOPS (ref C), pg IV-11-5, para 11.4.2.4 states: ``warning.
stall on one eng while maneuvering at low airspeed must be dealt with
immediately, since flight control effectiveness may be insufficient to
counter the YAW rate generated by asymmetric thrust.''
(CH) F-14A NATOPS (ref c), pg IV-11-5, para 11.4.2.2 states, ``Subsonic
compressor stalls are characterized by an RPM decrease and an increase in
TIT. They may produce an audible thump or bang, or they may be inaudible.''

(END PART ONE)

(continued)

(CI) Both left and right fuel shutoff valves in eng nacelle were confirmed in
the open (normal) position. (14a)
(CJ) Both left and right eng fuel feed systems showed no evidence of
preimpact failure. Analysis of fuel recovered from various Locations in the
engine accessory components indicated JP5 contaminated only with salt water
due to long immersion in ocean. (14a) (CK) there was no evidence of fod
ingestion in the leading edge on the inlet guide vanes on either eng. (14a)
(CL) There was no airfoil damage on the N-1 (low speed) turbine assembly or
on the turbine exit vanes on either eng. (14a)
(CM) Left eng combustion (hot section) components revealed normal thermal
deterioration for the 601 hours since last hot section (750 hour) inspection.
(14a)
(CN) Left eng main bearing packages indicated no preimpact discrepancies.
(14a)
(CO) Lleft eng mfc was properly trimmed and did not reveal evidence of
physical deterioration of internal working components. (14a) (cp) left eng
first stage turbine blade thermal analysis indicated leading edge temp for
The blades was determined to be in the 2000 to 2100 deg F range. Normal
leading edge temp for TF30-P-414A turbine blades are in the 1800-1900 deg F
range. The depot rejection criteria for overtemp is 2050 deg F.
(CQ) (P) The left eng hot section would not have passed its 750 hour hot
section inspection, due to overtemp condition. (14a)
(CR) elevated first stage turbine blade temp can result from engine stall
conditions (any cause) as well as overtrim, TT5 limiter malfunction, turbine
failures, loss of cooling airflow to the turbine assembly, etc. Once turbine
blade microstructure has been changed to reflect an overtemp condition it
will remain in that state. Therefore, it is impossible to determine when or
how often the above normal first stage blade temp occurred. (14a)
(CS) Left eng N-1 rotor ASSY RPM was estimated to be between 40 percent
minimum and 70-75 percent maximum. Left eng N-2 rotor assembly RPM was
estimated to be between 65 percent minimum and 80-85 percent maximum.
Typical rotor speeds at idle are approx 45 percent N-1 RPM and 70 percent
N-2 rpm. (14a)
(CT) EI could not determine if the N-1 and N-2 rotor speeds were matched
aerodynamically (normal operation) or in a stalled condition (aerodynamically
mis-matched rotors/ aerodynamically unstable rotors) prior to or at impact.
(14a)
(CU) The left eng was found to be fully capable of producing normal power at
impact. (14a)
(CV) There were no performance related discrepancies found on the right eng
during ei. (14a)
(CW) Right eng last throttle input was for zone five AB operation and eng was
operating normally and staged in zone five AB at impact. (14a)
(CX) Both left and right AICS inlet ramp actuators were intact and in the
fully stowed (retracted) position; normal for landing configuration, low
speed, subsonic flight. (19a)
(CA Horizontal tail authority mechanism was intact and in the unrestricted
position. (19a)
(DA) at time of impact, aircraft wings were in their full forward (twenty
degree) position; wing flaps and slats were symmetrically and fully extended
in the landing configuration; and primary flight controls were operating
normally. (19a)
(DB) engine stall warning/overtemperature detection is provided to the pilot
via two flashing stall lights (left stall, right stall) located on either
side of the heads up display and is coupled with an audible tone in the
pilot's headset. the detection system is activated when:
(1) TIT temperature exceeds 1215 deg C, or
(2) The ratio of TIT temperature (deg C) to
low-pressure fan speed (percent nl)
exceeds 17 (deg c/percent nl).,(19a)
(dc) (P) the tf-30 engine can be in a stalled
condition without illumination of the engine
stall warning lights.
11. analysis.
a. Aircrew factor - MC were not adequately rested for MF. Rejected. MP and
MR AA and 72 hour history indicate both received sufficient rest and
nourishment prior to MF.
b. Aircrew factor - MC violated MS SOP/NATOPS by failing to conduct adequate
flight brief. Rejected. Witness statements indicate thorough briefs were
conducted by division lead, section lead, and MC. MC discussed single eng
catapult procedures and low altitude ejection scenarios in their crew brief.
c.
Aircrew factor - MC failed to complete proper landing checklist. Rejected.
All available evidence including witness statements, MR statement, ILARTS
analysis, and EI of recovered airframe indicate MA was in proper landing
configuration.
D. Aircrew factor - MP's attempt to salvage overshooting approach with left
rudder led to reduced eng comp stall margin, contributing to left eng comp
stall. Accepted. CLSO and BLSO perceived MA left rudder input during WUOSX.
Stall margin was already reduced up to 26 percent on left engine due to MCB
system stuck in bleeds closed position. F-14A NATOPS manual (ref C), pg
IV-11-4, para 11.4.2.1 states: ``excessive sideslip, even at low
AOA, may result in compressor stalls anywhere in the aircraft flight
envelope.'' and, ``TF30 engines are prone to compressor stalls if high AOA is
combined with sideslip.'' MP was adjusting throttle settings in normal course
of the approach to decelerate ma to wings level on speed of 139 KIAS from
145-148 KIAS at the ninety. MA AOB during WUOSX was 42 to 45 deg. AMB
believes MP applied left rudder in attempt to correct for overshooting start.
Overcontrol of MA, reduced throttle setting, and sideslip, combined with the
MCB stuck in bleeds closed position contributed to comp stall of the left
eng. Based upon above analysis, AMB concludes MP overcontrolled MA in
attempt to salvage overshooting approach with left rudder, leading to
decreased eng stall margin and contributed to left eng comp stall.
Who: Aircrew, pilot at controls
What: Aircrew, landing phase, LSO
Controlled, afloat, attempted to
Salvage a poor approach
Why: performance, technical error, overcontrol
E. Aircrew factor - MP failed to execute proper single eng
Waveoff procedures. Accepted. Analysis shows MA departed controlled flight
at approx 20 units AOA, approx six seconds after waveoff. F-14A NATOPS (ref
C), pg V-15-2, states the following warning regarding single eng waveoff:
``...do not exceed 14 units AOA during waveoff or bolter. Simulator tests
verify MA was controllable to 20 units AOA, however when 20 units was
exceeded, departure rapidly occurred. AMB believes MP-was distracted by MA
close proximity to water, and by efforts to determine engine status, and
suffered breakdown in scan. MR did not see any illuminated eng stall warning
lights. AMB believes left eng stall warning light was not illuminated. MP's
selection of AB and input of right stick and full right rudder to counter
roll and YAW from asymmetric thrust led to task saturation. MP allowed MA
pitch attitude to slowly increase with addition of power vice referencing AOA
for proper single eng waveoff procedures. F-14 NATOPS (ref C), p V-15-1
states, ``single engine ... waveoff may be accomplished safely up to the
gross weight limits for two engine operation.'' Based on above analysis, AMB
concludes MP failed to follow NATOPS single eng waveoff procedures, exceeded
maximum safe AOA, and allowed ma to depart controlled flight at an
unrecoverable altitude, due to external distraction and cognitive saturation.
Who: Aircrew, pilot at controls.
What: Aircrew, landing phase, LSO
Controlled afloat, other, performed
Single eng waveoff improperly.
Why: Performance, failure of attention, distraction external.
Why: Performance, failure of attention, cognitive saturation.
F. Aircrew factor - MP failed to inform mr of single eng emergency.
accepted. R/C has no engine instrumentation. MP did not disclose MA
emergency to MR. MP had received F-14A act at FRS which included importance
of communication. MP's last ICS comm acknowledged MR ICS COMM at ninety.
AMB believes MP was analyzing eng indications and aircraft status during
final approach. MR did not see any illuminated eng stall warning lights.
AMB believes MP became distracted by low altitude and left YAW during
waveoff attempt and failed to communicate emergency to MR due to channelized
attention and task saturation. MC was in cold MIC during approach. Had MP
been hot MIC, communication would have required less effort, and MP would
possibly have informed MR of single engine condition. F-14A NATOPS, ref (c),
pg IV-11-23, notes, referring to single eng landings: ``the role of the rio
is critical in this regime. He should closely monitor a/s, bank angle,
altitude, and AOA throughout the approach.'' MR's lack of situational
awareness regarding MA status prevented MR from effectively contributing to
crew coordination during a critical single eng emergency. With no engine
instrumentation in the R/C, RIO must rely on ICS comm from pilot to be made
aware of single eng condition. Based on above analysis, AMB concludes MP
failed to communicate eng status to MR due to task saturation, channelized
attention and external distraction, resulting in lack of effective crew
coordination.
Who: Aircrew, pilot at controls.
What: Aircrew, failure of aircrew coordination, failed to communicate.
Why: Performance, failure of attention, cognitive saturation.
Why: Performance, failure of attention, channelized attention.
Why: Performance, failure of attention, distraction external.
G. Aircrew factor - MR failed to back up mp. rejected. MR maintained flight
parameters COMM to MP throughout landing pattern regarding A/S, altitude and
position. MR communicated status abeam, at the ninety, the forty five and
the start. MR's last comm to MP occurred on final approach approx ten
seconds prior to ejection, ``We're ten kts slow, let's get some power on the
jet.'' Whether in response to MR or in normal course of flying the approach,
MP added power. The critical flight parameter MP exceeded during single eng
waveoff was AOA. Since MR was unaware MA was single eng, normal approach
A/S, not AOA, was MR's primary scan item. Although MR made no additional
COMM after ten knots slow call, it is the AMB's opinion that further A/S
calls alone would not have influenced MP to reduce AOA. MP had selected AB,
had input right stick and rudder to maintain wings level and counter left YAW
>from asymmetric thrust. MP allowed pitch attitude and AOA to slowly increase
throughout the waveoff. MR perceived MA was under control and sensed ma
would fly away safely. LSO's maintained a continuous series of imperative
calls during last seven seconds of MF. AMB believes MP would not have heard
or responded to additional information from MR during this time. MR had avia
selected on tid. Had MR known ma was single eng, MR could have monitored and
communicated critical AOA information to MP, possibly leading to successful
recovery, or opportunity for wings level ejection. Lack of R/C engine
instrumentation, or COMM from mp regarding single eng condition prevented MR
>from providing proper backup.
H. Aircrew factor - MP failed to respond to LSO calls.
Rejected. MR states LSO waveoff and power calls were received. MP complied
in a timely fashion. MP added power on MA prior to waveoff. MP selected AB
almost simultaneously with three rapid ``waveoff'' calls and before first
``power'' call. MR did not hear ``raise your gear'' calls transmitted only
two seconds prior to aircraft stall and departure. No evidence indicates MP
attempted to retract landing gear. Landing gear require approx 9-15 seconds
to retract, thus drag reduction would not have time to take effect.
I. Aircrew factor - MP failed to make timely decision to eject. accepted.
mp was distracted externally, and fixated on determining engine and aircraft
status while countering YAW and roll from asymmetric thrust. MP instrument
scan broke down and MP failed to recognize in extremis situation. mp was
task saturated, delaying ejection decision. command ejection was initiated
by MR when ma departed controlled flight. Rapid left roll off at low
altitude combined with delay between R/C and F/C ejection sequence and left
lateral trajectory of MP ejection seat resulted in mp ejection occurring out
of envelope. Based on above analysis, amb concludes mp failed to make a
timely decision to eject due to external distraction, channelized attention
and cognitive saturation.
Who: Aircrew, pilot at controls
Wwhat: Aircrew, failed to make timely decision.
Why: Performance, failure of attention, distraction external.
Why: Performance, failure of attention, channelized attention.
Why: Performance, failure of attention, cognitive saturation.
J. Aircrew factor - MR failed to make timely decision to eject. Rejected.
MR was unaware of single eng condition, though MR knew something was wrong
with MA. MR states ejection criteria was based on altitude and sink rate.
MR felt ma flight path had stabilized and was going to fly away. MR was
evaluating altitude in reference to CV when MA departed controlled flight and
rapidly rolled left. MR initiated ejection immediately upon departure from
controlled flight coincident with CLSO ``eject'' comm. MR did not hear
``eject'' COMM from CLSO. In the opinion of the AMB, no information was
available to compel MR to initiate ejection any sooner.
K. Material factor - malfunction of primary flight controls rendered MA
uncontrollable. Rejected. EI of MA flight control and HYD systems failed to
reveal any preimpact failures. Horizontal tail authority mechanism was intact
and in unrestricted position. Wing sweep, flaps, slats, and landing gear
were in proper landing configuration. EI further shows primary flight
controls to be operating normally.
L. Material factor - during single eng waveoff, right eng failed to produce
adequate thrust to recover MA. Rejected. There were no performance related
discrepancies found on right eng during EI. Right eng was in AB during
waveoff attempt.
Right eng MFC was properly trimmed and right eng was operating in zone five
AB at impact. F-14 NATOPS (ref C), P V-15-1 states, ``single-engine ...
waveoff may be accomplished safely up to the gross weight limits for two
engine operation.''
M. Material factor - left eng AICS ramp system failure, caused left eng comp
stall in critical flight regime. Rejected. EI of left eng AICS components
reveal inlet ramp actuators and inlet ramps were intact and fully stowed in
the proper position.
N. material factor - left eng sustained catastro phic failure in critical
flight regime. Rejected. EI reveals no evidence of fod damage to leading
edge of inlet guide vanes or to low speed turbine. Both low speed and high
speed compressor and turbine sections were intact with no evidence of
internal failure. Left main eng bearings were examined with no,pre- impact
discrepancies observed. The left eng was found to be fully capable of
producing normal power at impact.
O. Material factor - faulty left eng MFC caused eng comp stall/failure in
critical flight regime. Rejected. EI of left eng MFC indicated MFC was
properly trimmed. MFC exhibited no evidence of physical deterioration of
internal working components.
P. material factor - MA fuel system malfunction caused left eng flame-out in
critical flight regime. Rejected. Fuel was not contaminated with other than
salt water, due to long ocean immersion. Both engines were receiving fuel at
impact. The left fuel shutoff valve was confirmed open, and the left fuel
feed system showed no evidence of preimpact failure. MR states mp reported
fuel state during approach and did not indicate any discrepancies.
Q. Material factor - left engine MCB system stuck in bleeds closed position,
reducing eng stall margin. Accepted. EI revealed that as received, the
fixed position of the directional linear control valve assembly of the MCB
system was in the bleeds closed position. The components of the directional
linear control valve assembly were found to be caked with a dark powder-like
debris. Debris was consistent with normal wear. Normal position for the MCB
during landing approach (landing gear down and throttle set at less than
military) is open, to allow greater engine stall margin. A stuck closed
assembly results in decreased stall margin of up to 26 percent. Based on
above analysis, AMB concludes although not sufficient alone to stall the eng,
this malfunction, combined with reduced throttle setting and sideslip,
contributed to left eng comp stall. component: directional control linear
bleed
Valve assembly
Mode: Stuck in bleeds closed position

Agent: wear debris.
R. Material factor - MA experienced radio COM failure. Rejected. MC heard
and responded to radio transmissions throughout MF. Last radio transmission
>from ma was MR ball call inside forty-five. MR states LSO waveoff and power
calls were received.
S. Material factor - MA experienced ICS failure. Rejected. MR and mp
communicated normally throughout MF. MP verbally acknowledged ICS call at
ninety.
T. Material factor - MA experienced PITOT static/AOA system failure (A/S,
altimeter, VSI, AOA, or approach indexers.) Rejected. MA had outstanding MAF
indicating R/C A/S was three kts slower than F/C. This discrepancy falls
within acceptable limits. Comparison of MR and CLSO statements verify ma
pattern altitude, attitude and A/S to be within normal parameters from abeam
to forty five.
U. Material factor - MP ejection system failed to operate properly.
Rejected. MP ejection seat gun fired and achieved normal rocket burn approx
0.4 seconds after MR seat, indicating normal command ejection. MP seat
ejected with MA in rapid left roll, approx 110 deg left AOB, 55 feet AGL.
Outside Martin Baker MK GRU-7A safe envelope. MP seat impacted water prior
to seatman separation, at approx 235 FPS. MP's ejection system worked as
designed until water impact damage interrupted normal operation. Impact
damage prevented release of MP survival kit lugs.
V. Supervisory factor - FRS failed to provide adequate single eng waveoff
training. Rejected. FRS syllabus includes SSE waveoff training during
FCLP's. Though MP's day-by-day FRS FCLP gradesheets are no longer available,
AMB is confident MP received SSE waveoff training in preparation for both Apr
94 and Jul 94 CQ attempts.
W. Supervisory factor - MS failed to provide single eng waveoff training.
Accepted in Aug 94, MP flew one practice emergency FCLP period in MS prior
to TSTA III at-sea period. FLT included SSE touch and go landings but no SSE
waveoffs. MP flew no practice emergency FCLP's in oct 94 prior to MF. MPIS
CQ simulator in Oct 94 included single eng approach but no single eng
waveoff. MF scenario of eng failure in approach turn, followed by waveoff,
requires a high level of situational awareness, proper instrument scan
(including AOA), and proper application of FLT controls to fly away safely.
Lack of recent single eng waveoff training reduced MP's proficiency in this
critical FLT regime, leading to poor situational awareness and improper
procedures. MS may have felt this training unnecessary due to MP's previous
FRS training. Additionally, lack of any documented F-14A landing pattern eng
comp stalls negated justification for this specific training. Based on above
analysis, AMB concludes ms failed to provide single eng waveoff training due
to complacency and unforeseeable problem.
Who: Supervisory, squadron, commanding officer.
What: Supervisory, failed to provide training.
Why: Failure of attention, complacency
Why: Decision error, problem not foreseeable.
X. Supervisory factor - FRS failed to disqualify MP for substandard
performance. Rejected. MP successfully completed all phases of FRS training
and met all qualifying standards. MP disqualified during first CQ attempt.
Between Jun 92 to Sep 94 25 percent of CAT I pilots disqualified during
initial CQ attempt. All qualified on subsequent attempts. MP qualified
during second CQ attempt and was ranked number three of seven CAT I pilots in
landing grades. FRS LSO stated mp was slightly above average and that MP
``should perform well in the fleet.''
Y. Supervisory factor - MS failed to provide MP adequate training in
preparation for CQ. Rejected. MP flew eight FCLP periods and eighty-seven
graded passes in two weeks prior to MF, more than any other MS pilot. MP's
last FCLP flight occurred day prior to MF. MP additionally completed two
simulators instructed by ms LSO within two weeks of MF. MS presented MP with
five CV/CQ procedures lectures during same period. MP had sufficient ground
and airborne training for CQ mission.
Z. Supervisory factor - MS failed to properly manage MC pairing. Rejected.
MP was best of five MS nugget pilots in landing grades during pervious
at-sea period. MP had 1024 hours flight time prior to F-14, and a solid
reputation. MS was not concerned with MP's overall performance. MR was
cruise experienced, and a designated NATOPS instructor. MS considered
performance, personality, ability, and experience level when assigning crew
pairing.
AA. Facilities factor - CVW LSO's failed to initiate timely waveoff.
Rejected. Because of MP's lack of experience in case I pattern, and in
combination with an approach that was out of standards, BLSO initiated early
waveoff.
AB. Facilities factor - LSO's failed to use proper LSO terminology after
waveoff. Rejected. LSO comm after ``roger ball'' included ``waveoff,''
``power,'' ``level your wings and climb,'' ``raise your gear,'' and
``eject.'' MP selected ab prior to first ``power'' call. ``Level your wings
and climb'' was cut out by CLSO echoing ``waveoff,'' and was not heard by MR.
``raise your gear,'' though not a standard LSO NATOPS call, was appropriate
at the time. U.S. Navy LSO school analysis supports LSO COMM was proper and
timely.
AC. Maintenance factor - MS maintenance control released down aircraft safe
for flight. Rejected. No outstanding MAF in MA maintenance records
constituted a downing discrepancy. R/C A/S discrepancy was within allowable
criteria for flight. Left eng AB time to stage, though long at five seconds,
was commensurate with normal wear and age of engine and within acceptable
limits for flight. Maintenance personnel statements and review of records
show MA was safe for flight and properly prepared for CV landings.

(end part two)

(continued)

12. Conclusions
A. Mishap narrative: MC flew as wingman during case II recovery for CQ
refresher. After normal break and landing pattern entry, MP commenced
approach turn. Computed wings level on speed was 139 KIAS. MR noticed
aircraft decelerating during approach turn from approx ten kts fast abeam to
eight kts fast at the ninety to ten kts slow during final approach. MP flew
WUOSX, 42 to 45 deg AOB. CLSO and BLSO observed MA exhibit noticeable left
YAW, which was perceived as MP applying left rudder to arrest overshoot. MP
reduced power to maintain on speed while rolling wings level. Additionally,
MCB system on left engine was stuck in bleeds closed position due to wear
debris. These factors combined to cause a left eng comp stall. During
postmishap recollection, MR remembered hearing an almost imperceptible
``pop,'' similar to a ``popcorn stall,'' prior to ma crossing ship's wake.
During final approach MR transmitted on ICS, ``we're ten knots slow, let's
get some power on the jet.'' MP did not respond verbally, but did add power.
There was no further ICS comm by MC during remainder of MF. As MA rolled
wings level at start, black smoke trail appeared from right eng only,
indicating left eng malfunction. MP did not inform MR of eng malfunction.
BLSO initiated waveoff verbally and visually for WUOSX. Black smoke trail
>from right eng ceased, indicating right eng staging to a/b. CLSO echoed
``waveoff'' twice, cutting out BLSO ``level your wings and climb.'' BLSO made
one ``power'' call, two ``raise your gear'' calls and a second ``power''
call. Throughout waveoff, left YAW and rod persisted. MP had applied right
stick and rudder to counter asymmetric thrust. MR did not observe any eng
stall warning lights. MP lost situational awareness, failed to scan AOA,
allowed pitch attitude to slowly increase and exceeded maximum controllable
AOA of 20 units. At approximately flight deck level, MA stalled, departed
controlled flight, and rolled rapidly left. CLSO called ``eject, eject'' as
MR initiated command ejection. MR and MP ejection seats both departed MA.
MR achieved seat-man separation and main parachute deployment. MP seat
fired outside safe ejection envelope, impacted water prior to seat-man
separation, damaging seat and interrupting seat sequence. The causal factors
of this mishap and injury are a result of overcontrol, external distraction,
cognitive saturation, channelized attention, wear debris, complacency and
problem not forseeable.
B. Causal factors of the mishap:
(1) The narrative cause factors of this mishap are Determined to be:
(A) Aircrew factor - MP attempt to salvage overshooting approach led to
reduced eng stall margin, contributing to left eng comp stall. RAC II.
(B) Aircrew factor - MP failed to execute proper single eng waveoff
procedures. RAC II.
(C) Aircrew factor - MP failed to inform MR of single eng emergency. RAC II.
(D) material factor - Left engine directional control valve stuck in bleeds
closed position.
RAC V.
(E) Supervisory factor - MS failed to provide single eng waveoff training.
RAC V.
(C) Causal factors causing other damage or injury:
(1) The narrative cause factors of other damage or injury are determined to
be:
(A) Aircrew factor - MP failed to make timely decision to eject. RAC I.
13. Recommendations.
A. Causal factors of the mishap:
(1) For COMNAVAIRSYSCOM:
(A) Direct one time fleet-wide inspection of F-14A, TF-30 engine mid
compression bleed system to include proper operation of directional control
linear bleed valve (solenoid) assembly.
(B) review previous recommendations for a newly designed directional control
linear bleed valve aSSEmbly, particularly the 1993 pratt and whitney
component improvement program action item chit design to alleviate wear.
(C) incorporate high-power trim box tests of tf-30 engines between 750 hr hot
section inspections, at 250 hrs and 500 hrs, to determine available thrust,
stall margin and proper operation of MCB system.
(2) For COMFITWINGPAC, COMFITWINGLANT:
(A) Add single eng landing configuration to annual OOC trainer syllabus.
(3) For F-14A model manager, VF-101:
(A) Add ``single engine failure, landing configuration'' procedures to F-14A
NATOPS manual (ref C), Chapter 14. Procedures should include warning
emphasizing importance of AOA during waveoff.
(B) During instructor/replacement act and act instructor designator syllabus,
increase emphasis on proper inter-cockpit communication.
(C) Add single engine failure/waveoff in landing pattern to FAM/CQ phase
simulator training. F-14A NATOPS manual (ref C), p. IV-16-2.
(4) For commanding officer, VF-213:
(A) Reevaluate criteria for selection of ICS hot MIC mode. Change SOP to
verbal acknowledgment of all ICS comms in critical FLT regimes.
(B) During annual act, reemphasize need for proper inter-cockpit
communication.
(C) Conduct simulated single engine waveoff practice during FCLP training.
(D) Conduct single engine waveoff practice in CQ simulator training.
B. Causal factors of other damage or injury:
(1) For F-14A model manager, VF-101:
(A) Incorporate and conduct ejection scenarios in FAM/CQ phase simulator
training.
(B) Add roll-angle ejection envelope charts to F-14A

(END MIR)

Enjoy folks, I gotta go for a few hours, but I'll be back.