# Boeing 737-2H5 - Type: Aircraft model (FAA registry) - Registry code: 138448E - Manufacturer (registry): BOEING - Model: 737-2H5 - Aircraft type: Fixed wing multi engine - Category: Airplane - Engines: 2 · Turbo-fan - Seats: 124 - Weight class: 20,000 lb and over - Cruise speed: 426 mph - Certification: Type certificated - Registered aircraft: 0 - Page: https://openairdocs.org/model/boeing-737-2h5 Model codes come from the FAA registry's reference file. ADs are matched to them by model name and maker. ## ADs that may apply (OpenAirDocs) Matched to this model by model name and maker. Each AD's applicability may narrow it by serial number, part number or equipment. None matched. ## Registered aircraft None registered with this model now. ## NTSB investigations (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB DCA96IA061](https://openairdocs.org/ntsb/DCA96IA061), Jun 10, 1996: Boeing B-737-201 (N221US), Richmond, VA, incident, no damage. Probable cause: The yaw/roll upset of the airplane resulting from the movement of the rudder surface to its blowdown limit. The rudder surface most likely deflected in a direction opposite to that commanded by the… ## FAA accident and incident reports (4) From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [Incident 19990517041489I](https://openairdocs.org/incident/19990517041489I), May 17, 1999: Boeing 7372H5 (N220US), Orlando, FL, Minor damage. (-23) On takeoff roll the aircraft lost power on number 2 engine. Aircraft aborted takeoff and returned to ramp. Visual inspection revealed heavy compressor… - [Incident 19960514018549I](https://openairdocs.org/incident/19960514018549I), May 14, 1996: Boeing 7372H5 (N221US), Trenton, NJ. Narrative: on 05/14/96 flight 411 took off from Trenton-Mercer County Airport (ttn) en route to bos. After levelling at 10,000 ft. and within 12-15 minutes the… - [Incident 19930914038059I](https://openairdocs.org/incident/19930914038059I), Sep 14, 1993: Boeing 7372H5 (N221US), Syracuse, NY. NR1 engine overheat light on. Diverted to Syracuse. Found 13th stage duct clamp broken. Replaced clamp. - [Incident 19890914048259I](https://openairdocs.org/incident/19890914048259I), Sep 14, 1989: Boeing 7372H5 (N220US), Worcester, MA. Improperly aligned with runway. Landed with left gear off runway. Broke two runway lights. ## Service difficulty reports (81, newest 50) As reported by operators and repair stations, by the model named in the report. - [SDR 99ZZZM403](https://openairdocs.org/sdr/99ZZZM403), May 17, 1999: ENGINE. LOST POWER. DURING TAKEOFF AT 80-90 KNOTS, NR 2 ENGINE LOST POWER, WAS SHUTDOWN AND TAKEOFF ABORTED. CAUSE UNDER INVESTIGATION AS TO FOD INGESTION OR NOT. (M) - [SDR 98ZZZX3002](https://openairdocs.org/sdr/98ZZZX3002), Jul 28, 1998: TURBINE. FAILED. ON TAKEOFF FROM GSO ON FLT 405 AT 500 FEET AGL, THE NR 1 ENGINE SHUT DOWN DUE TO APPARENT LPT FAILURE. THE TURBINE WAS CONTAINED AND NO FIRE OR OTHER DAMAGE OCC - [SDR 98ZZZX2562](https://openairdocs.org/sdr/98ZZZX2562), Jul 2, 1998: FLASHLIGHT. FAILED. DURING PRE-FLIGHT CHECK, THE F/A REPORTED THAT ONE OF THE 2 FLASHLIGHTS IN THE AFT GALLEY DID NOT BLINK WITHIN THE REQUIRED 7 SECONDS. PLACED FLASHLIGHT ON MEL - [SDR 98ZZZM494](https://openairdocs.org/sdr/98ZZZM494), May 27, 1998: POWER SUPPLY. INOPERATIVE. FORWARD LEFT (PAX) AND RT SERVICE DOOR EXIT EMERGENCY LIGHTS INOP. REMOVED AND REPLACED FORWARD EMERGENCY LIGHTS POWER SUPPLY PACK, S/N ON 1715, S/N OFF 15002, - [SDR 98ZZZM496](https://openairdocs.org/sdr/98ZZZM496), May 22, 1998: WIRE. CHAFED. EMERGENCY EXIT LIGHT PATH INOP. REPAIRED BROKEN WIRE UNDER SEAT 2ABC. (M) - [SDR 98ZZZM495](https://openairdocs.org/sdr/98ZZZM495), May 22, 1998: BULB. FAILED. FORWARD ENTRY DOOR EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED BULB. (M) - [SDR 98ZZZM401](https://openairdocs.org/sdr/98ZZZM401), Feb 26, 1998: SPLICE. BROKEN. ON OVERNIGHT CHECK, FOUND ROW 2 EMERGENCY LIGHT INOP. FOUND BUTT SPLICE BROKEN. REINSTALLED NEW SPLICE, OPS CHECK OK. (M) - [SDR 98ZZZX1075](https://openairdocs.org/sdr/98ZZZX1075), Feb 13, 1998: HYDRAULIC TUBE. CHAFED. FLT 992/23 NCO - LOST A-HYDRAULIC SYSTEM PRESSURE AND QUANTITY AFTER TAKEOFF CLIMBING THROUGH APPROX 3,500 FEET. COMPLETED EMERGENCY CHECK LIST. BURNED OFF EXCE - [SDR 98ZZZX900](https://openairdocs.org/sdr/98ZZZX900), Feb 4, 1998: STATOR. DAMAGED. DURING B-CHECK, NR 2 ENGINE INSPECTION FOUND FIRST STAGE COMPRESSOR STATOR VANE DAMAGE. ONE VANE HAD RIVETS SHEARED, VANE SHIFTED AND CAUSED DAMAGE TO ADJACENT - [SDR 98ZZZX902](https://openairdocs.org/sdr/98ZZZX902), Jan 25, 1998: POWER SUPPLY. INOPERATIVE. INTERIOR AND EXTERIOR EMERGENCY LIGHTS AT FORWARD ENTRY AND FORWARD SERVICE DOORS DO NOT ILLUMINATE. FOUND ON RON SVC CHECK. REPLACED EMERGENCY LIGHT BATTERY AN - [SDR 98ZZZX901](https://openairdocs.org/sdr/98ZZZX901), Jan 25, 1998: BATTERY. DISCHARGED. INTERIOR AND EXTERIOR EMERGENCY LIGHTS AT FORWARD ENTRY AND FORWARD SERVICE DOORS DO NOT ILLUMINATE. FOUND ON RON SVC CHECK. REPLACED EMERGENCY LIGHT BATTERY AN - [SDR 98ZZZM80](https://openairdocs.org/sdr/98ZZZM80), Dec 12, 1997: LIGHT. INOPERATIVE. FORWARD ENTRY DOOR EMERGENCY EXIT LIGHT INOP, FOUND ON RON MAINTENANCE CHECK. REPLACED LIGHT ASSY, OPS CHECK GOOD. (M) - [SDR 98ZZZM79](https://openairdocs.org/sdr/98ZZZM79), Dec 10, 1997: LIGHT. DAMAGED. L2 DOOR EMERGENCY EXITLIGHT DAMAGED DURING REAR STAIR EXTENSION DURING TRAINING EXCERISE. UNIT WAS REPLACED WITH FLT COMPT EMERGENCY EXIT LIGHT, DUE PART NIS. F - [SDR 97ZZZM1069](https://openairdocs.org/sdr/97ZZZM1069), Sep 11, 1997: TAB HINGE. WORN. VIBRATION FELT IN CONTROL YOKE AS WELL AS THROUGHOUT THE AIRCRAFT F/A'S STATE VIBRATION WAS MORE PROMINENT IN AFT OF AIRCRAFT, MORE PROMINENT ON RIGHT SIDE. INS - [SDR 97ZZZX2605](https://openairdocs.org/sdr/97ZZZX2605), May 7, 1997: POWER SUPPLY. INOPERATIVE. ON ROUTINE CHECK, OVERNIGHT INSPECTION, MAINTENANCE REPORTED AFT SERVICE DOOR EMERGENCY LIGHT INOPERABLE. REPLACED POWER SUPPLY. - [SDR 97ZZZM426](https://openairdocs.org/sdr/97ZZZM426), Mar 2, 1997: SKIN. CRACKED. FOUND 5 CRACKS AT FASTENERS STATION 373, 374, 375, 377, STRINGER 15L. REPAIRED PER SRM 53-30-3. (M) - [SDR 97ZZZM425](https://openairdocs.org/sdr/97ZZZM425), Mar 2, 1997: SKIN. CRACKED. FOUND .125 INCH CRACK AT FASTENER HOLE. REPAIRED PER SRM 53-30-1. - [SDR 97ZZZM424](https://openairdocs.org/sdr/97ZZZM424), Mar 2, 1997: SKIN. CRACKED. FOUND TWO .25 INCH LONG CRACKS. REPAIRED PER SRM 53-30-3 FIG 1. - [SDR 97ZZZM423](https://openairdocs.org/sdr/97ZZZM423), Mar 2, 1997: SKIN. CRACKED. FOUND TWO CRACKS AT FASTENER HOLES. REPAIRED PER SRM 53-30-3. - [SDR 97ZZZM422](https://openairdocs.org/sdr/97ZZZM422), Mar 2, 1997: FRAME. CRACKED. FOUND ONE INCH CRACK IN FRAME. REPAIRED PER SRM 51-40-2. - [SDR 97ZZZM421](https://openairdocs.org/sdr/97ZZZM421), Mar 2, 1997: FRAME. CRACKED. LEFT OUTBOARD CHORD ANGLE CRACKED STATION 1156 WL 274, .75 INCH CRACK. REPAIRED PER EO 5391G569. - [SDR 97ZZZM420](https://openairdocs.org/sdr/97ZZZM420), Mar 2, 1997: STRINGER. CRACKED. ONE INCH CRACK IN STRINGER. REPAIRED PER SRM 53-10-3. - [SDR 97ZZZM419](https://openairdocs.org/sdr/97ZZZM419), Mar 2, 1997: SKIN. DISBOND. SKIN DISBONDED AT LOWER CORNERS OF EMERGENCY EXIT APERTURE, REPAIRED PER EA 42068. - [SDR 97ZZZM418](https://openairdocs.org/sdr/97ZZZM418), Mar 2, 1997: SKIN. CRACKED. 3 INCH BY 5 INCH DELAMINATED AREA AND CRACKS AT SIX FASTENER HOLES. REPAIRED PER EA 42062. (M) - [SDR 97ZZZM417](https://openairdocs.org/sdr/97ZZZM417), Mar 2, 1997: BULKHEAD FITTING. CRACKED. BULKHEAD FITTING CRACKED 3 INCHES. TIME LIMITED REPAIR INSTALLED PER EA 42071 AND DWG 65C 29229. (M) - [SDR 97ZZZM245](https://openairdocs.org/sdr/97ZZZM245), Jan 27, 1997: SKIN. CORROSION. CLT - INSPECTION VISUALLY AND BY NDT/HFEC FOUND CORRODED AREA MEASURING APPROX 15 INCHES BY 20 INCH LOCATED AT FUSELAGE BS 312, STRINGER 27R AND BEAR STRAP AND - [SDR 97ZZZM244](https://openairdocs.org/sdr/97ZZZM244), Jan 27, 1997: STRINGER. CORROSION. CLT - INSPECTION VISUALLY, FOUND CORROSION APPROXIMATELY 14 INCH BY 20 INCH LOCATED AT BS 344, STRINGER 27R-28R. INSPECTION CARD NR J2C-40-5325-1, SSID/SIP REF - [SDR 97ZZZM23](https://openairdocs.org/sdr/97ZZZM23), Dec 5, 1996: CONNECTOR. SHORTED. NR 1 ENGINE FIRE WARNING CAME ON INTERMITTENTLY ON LANDING. FOUND DEFECTIVE CANNON PLUG, MANUFACTURERS PART NR 42839 KS 14S-5SX SHORTED. - [SDR 96ZZZX2793](https://openairdocs.org/sdr/96ZZZX2793), Apr 30, 1996: SKIN. CRACKED. GSO - VISUAL INSPECTION FOUND .9 INCH CRACK IN OUTER SKIN AT FS 767, STR 19R DURING WALK-AROUND. INSTALLED DOUBLER USING BLIND FASTENERS (OM-7 32938), PER SRM 5 - [SDR 96ZZZX1484](https://openairdocs.org/sdr/96ZZZX1484), Mar 1, 1996: SKIN. CRACKED. GSO - .1250 INCH CRACK AT RIVET HOLE FOUND. INSTALLED DOUBLER SRM 53-30-3, FIGURE 6. - [SDR 96ZZZX1483](https://openairdocs.org/sdr/96ZZZX1483), Mar 1, 1996: SKIN. CRACKED. GSO - FIVE .25 INCH CRACKS AT RIVET HOLES FOUND. INSTALLED REPAIR PER E.A. 40951. - [SDR 96ZZZX1482](https://openairdocs.org/sdr/96ZZZX1482), Mar 1, 1996: SKIN. CRACKED. GSO - 3 CRACKS FORWARD UPPER CORNER, FORWARD SERVICE DOORWAY. INSTALLED DOUBLER PER E.A. 40950. - [SDR E9WA](https://openairdocs.org/sdr/E9WA), Feb 16, 1996: SKIN. DAMAGED. CLT - INSPECTION VISUALLY FOUND MISSING TRAILING EDGE HONEYCOMB CORE MATERIAL LOCATED AT THE VERTICAL STAB AT RUDDER STATION 218 RIGHT TRAILING EDGE PANEL. COMP - [SDR 96ZZZM798](https://openairdocs.org/sdr/96ZZZM798), Feb 16, 1996: SKIN. DAMAGED. CLT - INSPECTION FOUND 2 PREVIOUSLY INSTALLED DOUBLERS WITH BLIND FASTENERS LOCATED AT FUSELGE SKIN, FS 727A AT STRINGER 15R AND 16R. INSTALLED EXTERNAL DOUBLER - [SDR 96ZZZM744](https://openairdocs.org/sdr/96ZZZM744), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND MEASURING 12 INCHES BY 2.5 INCHES LOCATED FUSELAGE SKIN AT STATION 927-947 AND STRINGER 14L. INST - [SDR 96ZZZM743](https://openairdocs.org/sdr/96ZZZM743), Feb 16, 1996: SKIN. CRACKED. CLT - INSPECTION VISUALLY FOUND A CRACK THROUGH RIVET .1875 INCH UP AND .125 INCH DOWN LOCATED AT FUSELAGE SKIN AT STATION 251 AND STRINGER 11L. INSTALLED DOUBL - [SDR 96ZZZM742](https://openairdocs.org/sdr/96ZZZM742), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND DISBONDED SKIN AND DOUBLER MEASURING 9 INCHES BY 5 INCHES LOCATED AT THE FUSELAGE SKIN AT STATION 288, STRINGER 14L AND ST - [SDR 96ZZZM741](https://openairdocs.org/sdr/96ZZZM741), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND DISBONDED SKIN AND DOUBLER AT THE FUSELAGE SKIN MEASURING 5 INCHES BY 18 INCHES LOCATED AT STATION 920 TO 927 AND STRINGER - [SDR 96ZZZM740](https://openairdocs.org/sdr/96ZZZM740), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND LOCATED AT FUSELAGE SKIN MEASURING 3 INCHES BY 4 INCHES AT STATION 967 ABOVE STRINGER 5L. INSTALL - [SDR 96ZZZM739](https://openairdocs.org/sdr/96ZZZM739), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND LOCATED AT FUSELAGE SKIN MEASURING 5 INCHES BY 4 INCHES AT STATION 356, STRINGER 15L AND 16L. INS - [SDR 96ZZZM738](https://openairdocs.org/sdr/96ZZZM738), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND SKIN AND DOUBLER DISBOND LOCATED AT FUSELAGE SKIN MEASURING 14 INCHES BY 2.5 INCHES AT STATION 902 TO 914 AND STRINGER 13R - [SDR 96ZZZM737](https://openairdocs.org/sdr/96ZZZM737), Feb 16, 1996: SKIN. CRACKED. CLT - INSPECTION VISUALLY FOUND AND VERIFIED WITH HFEC A 1.25 INCH CRACK LOCATED AT FUSELAGE SKIN FS 1137 AND STRINGER 12L. INSTALLED DOUBLER AS PER BOEING SRM - [SDR 96ZZZM736](https://openairdocs.org/sdr/96ZZZM736), Feb 16, 1996: SUPPORT BEAM. CORROSION. CLT - INSPECTION VISUALLY FOUND LEVEL I CORROSION AT THE FUSELAGE FLOOR SUPPORT BEAM LOCATED AT LBL 2 TO LBL 6 AND STATION 1014. FABRICATED REPLACEMENT H-CHANNE - [SDR 96ZZZM735](https://openairdocs.org/sdr/96ZZZM735), Feb 16, 1996: SKIN. GOUGED. CLT - INSPECTION VISUALLY FOUND A 1.5 INCH GOUGE .019 DEEP AT FUSELAGE SKIN LOCATED AT FS 360 1 INCH ABOVE STRINGER 18L. INSTALLED DOUBLER AS PER BOEING SRM 53- - [SDR 96ZZZM734](https://openairdocs.org/sdr/96ZZZM734), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC FOUND DISBONDED SKIN AND DOUBLER AT THE FUSELAGE SKIN LOCATED AT STATION 927 TO 947 AND STRINGER 21R TO STRINGER 20R. REMOVED AND - [SDR 96ZZZM733](https://openairdocs.org/sdr/96ZZZM733), Feb 16, 1996: SKIN. CORROSION. CLT - INSPECTION VISUALLY FOUND A LEVEL I CORRODED PRODUCTION STRINGER SPLICE 6 INCHES AT THE FUSELAGE SKIN LOCATED AT STATION 908 AND STRINGER 20R. REPLACED AN - [SDR 96ZZZM732](https://openairdocs.org/sdr/96ZZZM732), Feb 16, 1996: SKIN. DISBONDED. CLT - INSPECTION VISUALLY FOUND 6 INCH DISBONDED FUSELAGE SKIN LOCATED AT STATION 954 BETWEEN STRINGER 24 AND STRINGER 23R. REPLACED SKIN AS PER USAIR EA NR 580 - [SDR 96ZZZM731](https://openairdocs.org/sdr/96ZZZM731), Feb 16, 1996: ANGLE. CRACKED. CLT - INSPECTION VISUALLY FOUND A 1.5 INCH CRACK LOCATED AT THE FUSELAGE RADIUS OF ANGLE AT FS 1085 AND STRINGER 2L. INSTALLED AND MANUFACTURED ANGLE AS PER BOE - [SDR 96ZZZM730](https://openairdocs.org/sdr/96ZZZM730), Feb 16, 1996: SKIN. DISBOND. CLT - INSPECTION BY ULTRASONIC, FOUND TWO 6 INCHES BY 6 INCHES AND 8 INCHES BY 2 INCHES AREAS OF SKIN AND DOUBLER DISBOND LOCATED AT THE FUSELAGE SKIN BETWEEN S - [SDR 96ZZZM729](https://openairdocs.org/sdr/96ZZZM729), Feb 16, 1996: SKIN. DISBONDED. CLT - INSPECTION BY ULTRASONIC, FOUND FUSELAGE SKIN AND DOUBLER DISBOND LOCATED AT STATION 927 TO 947, STRINGER 9L AND STRINGER 10L. INSTALLED FIELD DOUBLERS AS All 81: https://openairdocs.org/model/boeing-737-2h5/reports.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.