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Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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F-35 evaluation by US military's testing community.

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Page 1: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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F-35 Joint Strike Fighter (JSF)

Page 2: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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Actual versus Planned Test Metrics through October 2013TEST FLIGHTS

All Testing Flight Sciences Mission SystemsAll Variants F-35B Only F-35A Only F-35C Only

2013 Actual 993 284 226 181 302

2013 Planned 985 287 241 171 286

Di!erence from Planned +0.8% -1.0% -6.2% +5.8% +5.6%

Cumulative Actual 3,601 1,269 963 612 757

Cumulative Planned 3,284 1,127 910 584 663

Di!erence from Planned +9.7% +12.6% +5.8% +4.8% +14.2%

TEST POINTS

All Testing Flight Sciences Mission Systems

All Variants F-35B Only F-35A Only F-35C Only Block 1* Block 2A Block 2B Block 3 Other

2013 Baseline Accomplished 5,464 1,418 1,713 1,032 326 168 461 0 346

2013 Baseline Planned 7,180 1,701 1,836 1,165 1,755 0 723

Di!erence from Planned -23.9% -16.6% -6.7% -11.4% -45.6% -52.1%

Added Points 1,776 178 193 211 1,194 0 0

Points from Future Year Plans 720 320 0 400 0 0 0

Total Points Accomplished** 7,960 1,916 1,906 1,643 2,149 0 346

Cumulative SDD Baseline Actual 26,689 9,356 7,636 5,859 1,166 614 860 0 1,198

Cumulative SDD Baseline Planned 27,075 9,256 7,735 5,564 2,663 0 1,857

Di!erence from Planned -1.4% +1.1% -1.3% +5.3% -0.9% 0.0% -35.5%

Program O"ce Estimated Test Points Remaining 31,218 9,726 6,057 7,493 350 606 3,226 1,739 2,021

* Includes Block 0.5 and Block 1 quantities** Total Points Accomplished = 2013 Baseline Accomplished + Added Points

SDD = System Development and Demonstration

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Page 3: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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F#35B DOOR AND PROPULSION PROBLEMS

Category Component Problem Design Fix and Test Status Production Cut-In

Structure Auxiliary Air Inlet Door (AAID)

Inadequate life on door locks, excessive wear and fatigue due to the bu!et environment, inadequate seal design.

New designed doors are being installed on low-rate initial production (LRIP) aircraft as part of the ongoing modi"cation plan; "ve completed through the end of September. Fatigue testing started in November 2012 and has completed just over 6 percent of the planned two lifetimes of testing as of end of September.

BF-38 LRIP 62014

Propulsion Drive Shaft

Lift fan drive shaft undergoing a second redesign. Original design was inadequate due to shaft stretch requirements to accommodate thermal growth, tolerances, and maneuver de$ections. First redesign failed quali"cation testing.

New design of the drive shaft will begin quali"cation testing in December. Full envelope requirements are currently being met on production aircraft with an interim design solution using spacers to lengthen the early production drive shaft.

BF-50 LRIP 82016

Propulsion ClutchLift fan clutch has experienced higher than expected drag heating during conventional (up and away) $ight during early testing.

New clutch plate design, with more heat-tolerant material, is complete. Clutch plates are being thinned on LRIP 5 and 6 aircraft, at the expense of reduced life (engagements) to the clutch, to prevent drag heating.

BF-44 LRIP 72015

Propulsion Roll Post Nozzle Actuator

Roll post nozzle bay temperatures exceed current actuator capability; insulation is needed to prevent possible actuator failure during vertical lift operations.

Insulation between the roll post nozzle bay and the actuators is being installed in pre-LRIP 7 aircraft to allow unrestricted operations; however, the actuators must be replaced at 1,000-hour intervals. New actuators will be installed in LRIP 7 aircraft and beyond, removing the requirements for the insulation and extending the service life to 4,000 hours.

BF-44 LRIP 72015

Propulsion Bleed Air Leak Detectors

Nuisance overheat warnings to the pilot are generated because of poor temperature sensitivity of the sensors; overheats are designed to be triggered at 460 degrees F, but have been annunciated as low as 340 degrees F.

More stringent acceptance test procedures are in place, requiring the sensors to be more accurate. Maintenance personnel are checking the detectors on pre-LRIP 5 aircraft, and replacing them in accordance with directives, if necessary.

BF-35 LRIP 52014

Propulsion

Aux Air Inlet Door Aft down-lock seal doors (aka "saloon

doors")

Doors are spring-loaded to the closed position and designed as overlapping doors with a 0.5- inch gap. The gap induces air $ow disturbance and make the doors prone to damage and out-of-sequence closing. Damage observed on $ight test aircraft.

Springs are being limited to 4,000 hours or half the planned lifetime. Program continues to investigate whether a new design to the doors is required.

TBD

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Issues A!ecting Operational Suitability2YHUDOO�VXLWDELOLW\�SHUIRUPDQFH�FRQWLQXHV�WR�EH�LPPDWXUH��DQG�UHOLHV�KHDYLO\�RQ�FRQWUDFWRU�VXSSRUW�DQG�ZRUNDURXQGV�XQDFFHSWDEOH�IRU�FRPEDW�RSHUDWLRQV���$LUFUDIW�DYDLODELOLW\�DQG�PHDVXUHV�RI�UHOLDELOLW\�DQG�PDLQWDLQDELOLW\�DUH�DOO�EHORZ�SURJUDP�WDUJHW�YDOXHV�IRU�WKH�FXUUHQW�VWDJH�RI�GHYHORSPHQW���

F-35 Fleet Availability�� $YHUDJH�)����DYDLODELOLW\�UDWHV�IRU�RSHUDWLRQDO�XQLWV�DUH�

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F#35 AVAILABILITY FROM NOVEMBER 2012 THROUGH OCTOBER 2013*

Operational Site Average Maximum Minimum

Whole Fleet 37% 46% 26%

Eglin F-35A 38% 51% 24%

Eglin F-35B 39% 54% 22%

Eglin F-35C ** 32% 61% 13%

Yuma F-35B 29% 45% 6%

Edwards F-35A 29% 41% 14%

Nellis F-35A 37% 63% 14%

* Data do not include SDD aircraft** Eglin F-35C data began in August 2013

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Page 16: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

D O D P R O G R A M S

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F#35 RELIABILITY AS OF AUGUST 31, 2013 $ MFHBCF, HOURS

Variant

Requirement Current ValuesObserved MFHBCF as of May

2012Threshold MFHBCF

Threshold Flight Hour

Target

Observed MFHBCF

Current Total Flight Hours

Objective MFHBCF

from Growth Curve

Observed as % of

Objective Value

F-35A 20 75,000 4.5 4,204 13.5 33% 5.9

F-35B 12 75,000 3.0 3,286 7.7 39% 4.2

F-35C 14 50,000 2.7 903 9.0 30% 6.7

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HIGH DRIVER COMPONENTS AFFECTING LOW AVAILABILITY & RELIABILITY

Speci%c to Variant Common to All Variants

F-35Aassembly

system

helmet

System

F-35B actuator

tire assembly

F-35C assembly

Maintainability�� 7KH�DPRXQW�RI�WLPH�UHTXLUHG�WR�UHSDLU�IDLOXUHV�IRU�DOO�

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F#35 MAINTAINABILITY AS OF AUGUST 31, 2013 # MCMTCF &HOURS'

Variant Threshold Observed % of Threshold

FY12 Annual Report

F-35A 4.0 12.1 303% 9.3

F-35B 4.5 15.5 344% 8.0

F-35C 4.0 9.6 241% 6.6

F#35 MAINTAINABILITY AS OF AUGUST 31, 2013 # MTTR &UNSCHEDULED'

Variant Threshold Observed % of Threshold

FY12 Annual Report

F-35A 2.5 9.2 366% 4.2

F-35B 3.0 8.9 294% 5.3

F-35C 2.5 7.7 307% 4.0

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Page 17: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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WKH�)���$�DQG�)���%�LV�ODUJHO\�FRPSOHWH���9HUL¿FDWLRQ�QDWXUDOO\�ODJV�EHKLQG�GHYHORSPHQW��EXW�LV�SURJUHVVLQJ�WRZDUG�FRPSOHWLRQ���9HUL¿FDWLRQ�RI�PRGXOHV�UHTXLULQJ�H[WHQVLYH�LQWUXVLRQ�LQWR�WKH�DLUFUDIW�LV�SODQQHG�WR�EH�FRPSOHWHG�GXULQJ�GHSRW�OHYHO�PRGL¿FDWLRQV�RU�RSSRUWXQLVWLF�PDLQWHQDQFH���7KH�)���&�ODJV�EHKLQG�WKH�RWKHU�YDULDQWV��EXW�LV�SURFHHGLQJ�TXLFNO\�EHFDXVH�RI�YDULDQW�VLPLODULWLHV���7KH�FKDUW�EHORZ�VKRZV�WKH�VWDWXV�RI�-7'�GHYHORSPHQW�DQG�YHUL¿FDWLRQ�IRU�HDFK�YDULDQW��SURSXOVLRQ��VXSSRUW�HTXLSPHQW��DQG�VXVWDLQDEOH�ORZ�REVHUYDEOH��6/2��PDLQWHQDQFH���5HVXOWV�H[FOXGH�-7'�IRU�SLORW�ÀLJKW�HTXLSPHQW�DQG�-7'�XQLTXH�WR�/5,3�DLUFUDIW��VXFK�DV�VWUXFWXUDO�¿HOG�UHSDLUV��WKDW�ZLOO�QRW�EH�QHHGHG�IRU�IXOO�UDWH�SURGXFWLRQ�DLUFUDIW���)URP�2FWREHU������WR�2FWREHU�������WKH�3URJUDP�2I¿FH�YHUL¿HG�������DLUFUDIW�DQG�����SURSXOVLRQ�PRGXOHV���(DUO\�LQ�������WKH�SULPDU\�IRFXV�LQ�-7'�YHUL¿FDWLRQ�ZLOO�EH�ZHDSRQV�DQG�VWRUHV�

Data Modules Identi%ed

(as of Oct 2013)

Data Modules Completed

% Data Modules

Completed

% Data Modules Veri%ed

F-35A1 4,404 4,045 91.9% 81%

F-35B1 5,314 4,766 89.7% 76%

F-35C1 4,514 3,357 74.4% 55%

Propulsion 2,892 2,861 98.9% 94%

SE 2,241 489 21.8% 13%

SLO 1,362 291 21.3% 3%

Total 20,727 15,809 76.3% 64%Note: 1. Includes "eld and depot-level JTD for Operations and Maintenance (O&M) for air vehicle only

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Page 19: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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Page 20: Director, office of test and evaluation, 2013 report on Lockheed Martin F-35

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