# TCDS H40NM: Erickson Air-Crane Incorporated DBA Erickson Air-Crane

- Type: Type certificate data sheet
- Status: Current
- Holder: Erickson Air-Crane Incorporated DBA Erickson Air-Crane
- Revision: 6
- Revised: March 28, 2007
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21
- Data sheet PDF: https://openairdocs.org/files/sha256/4f/fc/4ffc2248d21c2bf6d2468d0876aac8a7e10df952d601715aef9541e627be862a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/D85FDE58AF13F263862585CB0058F2BB.0001
- Page: https://openairdocs.org/tcds/H40NM

## Models (1)

As the data sheet lists them.

- CH-54A

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2 3 4 5 6 7 
Rev. No. 6 6 6 6 6 6 6 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
H40NM 
Revision 6 
ERICKSON AIR-CRANE INCORPORATED 
CH-54A 
 
March 28, 2007 
 
TYPE CERTIFICATE DATA SHEET NO. H40NM 
 
This data sheet, which is a part of Type Certificate No. H40NM, prescribes conditions and limitations under which the product 
for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate (TC) Holder: Erickson Air-C rane Incorporated, DBA Erickson Air-Crane 
    3100 Willow Springs Road 
    P. O. Box 3247 
    Central Point, Oregon 97502 
 
 
Type Certificate Holder Record: Columbia Helicopter s, Inc. transferred TC H40NM (Restricted) to 
    Erickson Air-Crane Incorporated on April 14, 2005. 
 
I - Model CH-54A (Restricted Category) Approved October 22, 1992 (See Note 6) 
 
     Engines  2 Pratt & Whitney JF TD12A-4A (T73-P-1) (See NOTES 8 and 9) 
 
     Fuel Aviation Kerosene JP4 or JP5 
 
     Engine limits 
   Shaft               Power Turbine  Gas Gen.      Power Turbine 
   H.P. Speed (N 2) Speed (N 1) Inlet (T 5) 
   Military Power 4500     105%     104%    688 °C  
    (30 min.)  
 Normal Continuous 4000     104%     104%   655 °C 
    Cruise 
 
     Rotor limits  Maximum 204 r.p.m. (110% N r) 
 Minimum 167 r.p.m.  ( 90% N r) 
 
     Airspeed limits  Never Exceed:   99 kt. between 38,000 lb. and 42,000 lb. gross weight 
 (IAS)    115 kt. up to 38,000 lb. gross weight 
 
     C.G. range 324.0 to 352.0 at 23,000 lb. 
 324.0 to 352.0 at 30,000 lb. 
 328.0 to 352.0 at 38,000 lb. 
 328.0 to 346.0 at 38,000 lb. 
 328.0 to 346.0 at 42,000 lb. 
 Straight-line variation between points given

H40NM 2 
23,000
30,000
38,000
42,000
Gross
Weight
(Pounds)
324 328 346 352
INCHE S FROM DATUM
 
 
     Datum 336 inches forward of main rotor centroid. 
 
     Leveling means     Plumb line fro m top level plate inside cockpit aft door. 
 
     Maximum weight 42,000 lb. 
 
     Minimum crew 2 (pilot and co-pilot). 
 
     Number of seats 5:  2 at (+92.9), 1 at (+108.5), 1 at (+127.0), 1 at (+130.0). 
 
     Maximum cargo See NOTE 5. 
 
     Fuel capacity 1351 gal.; 454 gal. at (+ 280.8), 454 gal. at (+397.3), 443 gal at (+461.3). 
 
     Oil capacity 3.2 gal. at (+234.0)  (2 tanks 1.6 gal. each). 
 
     Rotor blade and For rigging information, see NOTE 8. 
     control movements 
 
     Other operating See NOTE 4. 
     limitations 
 
     Serial numbers eligible There are no eligible serial numbers at this time. 
 
 Certification basis FAR 21.25(a)(2) a nd (b) effective February 1, 1965, including amendments 21-1 through 21-42.  
Type Certificate No. H40NM issued October 22, 1992, for the Special Purpose of carriage of 
external loads in accordance with FAR 133.  Date of application for Type Certificate:  April 1, 
1992. 
 
 Production basis None.  Prior to certification of each ai rcraft, an FAA representative must perform a detailed 
inspection for workmanship, materials, and conformity with approved technical data, and will 
verify that a maintenance flight test has been completed for each aircraft by qualified maintenance 
personnel in accordance with the Department of the Army Technical Manual TM 55-1520-217-
MFT-1, dated June 17, 1985. 
 
     Equipment      Equipment necessary for the par ticular special-purpose operation must be installed (see NOTE 5). 
 
NOTE 1. A current weight-and-balance report including a list of equipment included in the certificated empty weight and  
 loading instructions, when necessary, must be in each helic opter at the time of original airworthiness certification  
 and at all times thereafter. 
 
NOTE 2. The following placard must be prominently disp layed in the cockpit in full view of the pilots: 
 
   "THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH  
  THE RESTRICTED CATEGORY OPER ATING LIMITATIONS OF FAR 91.313"

3 H40NM 
 
NOTE 3. The Maximum Allowable Operating Time (MAOT) schedule for Service Life-Limited Part overhaul and  
 retirement intervals are specified in Chapter 1, S ection VI of Technical Manual No. TM 55-1520-217-23-1,  
 "Aviation Unit and Intermediate Maintenance Manual CH -54A Helicopter," with Changes 1 through 21, dated  
 September 23, 1987, as supplemented w ith the life limits specified herein.  Refer to Department of the Army  
 Memorandum HQ, AVSCOM, AMSAV-ECC (702-3b), dated July 9, 1991, for a listing of MAOT extensions  
 for CH-54A, gearboxes, engines, main rotor and tail roto r heads.  MAOT extensions were granted individually  
 for certain CH-54A T73 engines in accordance with Department of the Army AVSCOM (AMSAV-EP) letters. 
 
MAXIMUM ALLOWABLE OPERATING TIMES  
for 
MAIN ROTOR HEAD P/N's S6410-20004-029, -031, -035 
 
 ITEM  NOMENCLATURE  PART NUMBER  RETIREMENT INTERVAL  
 
   1 Upper plate 6410-23011-101   3000 
   2 Lower plate 6410-23009-101    3000 
   3 Spacer 6410-23016-041    9000 
   6410-23006-012    4175 
   4 Hub 1510-23001-4    1030 
   5 Sleeve locknut 1510-23357-1  18300 
   6 ROT SWPLT 6410-24002-102    4560 
   7 Spindle locknut 1510-23031-1  10500 
   1510-23031     750 
   8 Sleeve 1510-23351  10200 
   9 Spindle 1510-23027-4    5675 
 10 Control horn 1510-23350-2    1600 
 11 Horiz. hinge pin 1510-23099-1    3500 
 12 Vertical hinge pin 1510-23022    2800 
 13 Primary servo 1565-20421-010    5050 
 14 Primary servo 1565-20421-011    5050 
 15 Primary servo 1565-20421-041    5050 
 16 Primary servo 1565-20421-042    5050 
 
NOTE 4. These helicopters must be operated in accordance with  a Rotorcraft Flight Manual comprised of the following: 
 
 (1) Department of the Army Technical Manua l No. TM 55-1520-217-10-1, "Operator's Manual,  
  Army Model CH-54A Helicopters," dated April 8, 1977,  with Changes 1 through 8; revised September 25,  
  1986. 
 
 (2) Department of the Army Technical Manual No . TM 55-1520-217-CL-1, "Operator's & Crewmember's  
  Checklist, Army Model CH-54A Helicopter s, Pilot's Checklist," dated June 2, 1985. 
 
 Day/VFR Restricted Category operations only. 
 
NOTE 5.  Provisions for the carriage of external loads are availa ble in the form of structural hard points on the fuselage  
  and main landing gear; single and four-point hoists; and a four-point load-leveler suspension system.   
  Information concerning the operati ng limitations with this equipment is contained in the Flight Manual. 
 
NOTE 6.  Prior to civil airworthiness certification, the fo llowing Department of the Army Modification Work Orders  
  (MWO) must be incorporated: 
 
MWO 55-1520-217-20-1 Incorporation of an improved c oupler spring device (CH-54A Helicopter), dated 
May 1, 1968. 
 
MWO 55-1520-217-20-4 Incorporation of an improved oil tr ansmitter restrictor (CH-54A Helicopter), dated  
 November 21, 1968. 
 
MWO 55-1520-217-30-7 Incorporation of inspection port in  main gearbox oil cooler blower and transition 
duct (CH-54A Helicopter), dated October 11, 1968.

H40NM 4 
MWO 55-1520-217-30-11 Engine Pressure Ratio (E.P.R.) system improvement (CH-54A Helicopter), dated 
February 27, 1968. 
 
MWO 55-1520-217-30-12 Incorporation of AFCS pedal switches, dated July 12, 1968. 
 
MWO 55-1520-217-30-19 Modification to avert 1 st and 2nd-stage servo system physical interference with 
primary servo armor (CH-54A Helicopter), dated August 16, 1968. 
 
MWO 55-1520-217-30-20 Change in the sensitivity of the fi re surveillance test circuit (CH-54A Helicopter), 
dated July 25, 1968. 
 
MWO 55-1520-217-30-22 Incorporation of a redesigned adapte r in all flight control-rod assemblies (CH-54A  
 Helicopter), dated October 9, 1967. 
 
MWO 55-1520-217-30-23 Installation of improved main la nding gear wheels (CH-54A Helicopter), dated  
 October 13, 1968. 
 
MWO 55-1520-217-30-25 Change of pressure switch assemb ly in auxiliary tank low fuel warning light 
system (CH-54A Helicopter), dated June 14, 1968. 
 
MWO 55-1520-217-30-29 Installation of improved right-hand flight control-rod assembly and modification 
of the right-hand oil cooler support strut assembly (CH-54A Helicopter), dated February 5, 1968. 
 
MWO 55-1520-217-30-30 Improved electrical wiring insta llation for main hoist cable cutter (CH-54A 
Helicopter), dated April 18, 1969. 
 
MWO  55-1520-217-30-34 Retrofit improvements to increase aft pilot visibility (CH-54A helicopters), dated 
January 5, 1970. 
 
MWO 55-1520-217-30-37 Incorporation of redundant elect rical circuit for cargo hook release system  
 (CH-54A Helicopter), dated January 10, 1973,  with Change 1, dated May 2, 1973.  
 
MWO 55-1520-217-30-39 Design improvements in cargo ha ndling system (CH-54A Helicopter), dated 
January 25, 1974. 
 
MWO 55-1520-217-30-45 Incorporation of strengthened c ontrol-rod assembly (CH-54A Helicopter), dated 
October 1, 1970. 
 
MWO 55-1520-217-30-48 Incorporation of an improved c ontrol speed setting actuator (CH-54A Helicopter), 
dated October 26, 1971. 
 
MWO 55-1520-217-30-51 Incorporation of magnecraft relay in the pilot's and copilot's turn and bank 
indicator circuitry (CH-54A Helicopter), dated September 8, 1972, with Change 1, dated  
 November 16, 1972. 
 
MWO 55-1520-217-30-54 Improved main gearbox oil pressure -switch assembly (CH-54A Helicopter), dated  
 September 17, 1976. 
 
MWO 55-1520-217-30-55 Fire surveillance system im provements (CH-54A/B Helicopters) dated  
 November 30, 1976, with Cha nge 1, dated August 9, 1983. 
 
MWO 55-1520-217-30-56 Improvements to cargo hook rel ease system (CH-54A Helicopter), dated  
 January 31, 1974. 
 
MWO 55-1520-217-30-57 Improved bearing support assemblies for the tail rotor drive shafting (CH-54A/B  
 Helicopters), dated September 30, 1976. 
 
MWO 55-1520-217-30-60 Relocation of rotor brake hydrau lic package and supporting bracket (CH-54A/B  
 Helicopters), dated July 9, 1976, with  Changes 1 and 2, dated May 18, 1984.

5 H40NM 
MWO 55-1520-217-30-61 Incorporation of APP hydraulic start system improvement (CH-54A/B 
Helicopters), dated June 14, 1977.   
 
MWO 55-1520-217-30-63 Incorporation of self-locking bolts  in the engine and flight control systems  
 (CH-54A/B Helicopters), dated July 21, 1981,  with Change 1, dated August 9, 1983. 
 
MWO 55-1520-217-30-69 Incorporation of strengthened bulkh ead at station 248, and a lower fuselage access 
panel (CH-54A/B Helicopters), dated October 25, 1982. 
 
MWO 55-1520-217-40-1 Incorporation of design improve ment to strengthen pylon assembly (CH-54A 
Helicopter), dated January 15, 1973. 
 
MWO 55-1520-217-40-3 Incorporation of improved hydraulic  manifold fittings and hydraulic line routing 
(CH-54A Helicopter), dated October 4, 1972, with Change 1, dated August 8, 1973. 
 
MWO 55-1520-217-40-4 Incorporation of improved vertical  gyro indicating system (CH-54A Helicopters), 
dated January 1, 1974. 
 
MWO 55-1615-236-20-1 Incorporation of an improved main rotor blade tip cap with nickel plate leading 
edge (CH-54A Helicopter), dated February 25, 1971. 
 
MWO 55-1615-248-20-1 Incorporation of strengthened tail rotor pitch link assembly (CH-54A Helicopter), 
dated March 22, 1971, with Change 1, dated May 13, 1971. 
 
MWO 55-1615-255-30-1 Improved attachment bolts for the CH -54B main rotor blades and the CH-54A/B tail 
rotor blades (CH-54A/B Helicopters), dated April 4, 1974, with Change 1, dated November 14, 1977. 
 
MWO 55-1680-276-30-1 Update cargo hoist (6435-63000-018 or 6435-63000-019) to accept cable 
 (6435-63090-101), (CH-54A Helicopter), dated Sept ember 18, 1970, with Change 1, dated  
 November 5, 1970. 
 
MWO 55-2840-230-20-1 Replacement of accessory and component drives gearbox main oil strainer cover 
and oil-pressure relief valve (T73-P-1 and T-73-P-700 turbo shaft engines), dated March 10, 1972. 
 
MWO 55-2840-230-30-1 Installation of fuel pressurizi ng and dump valve vibration damping bracket  
 (T73-P-1/700 Engines) for CH-54A/B Aircraft, da ted October 10, 1982; except that engine Serial 
Number P672458 may be operated until overhaul provided the area prescribed in MWO  
 55-2840-230-30-1 is inspected for cracks at the form al FAA screening inspection and thereafter, at 
 25-hour intervals, until overhaul (in approximately 90 hours). 
 
MWO 55-2840-230-30-2 Installation of improved design for lubr ication and alignment of fuel control flexible 
shaft assembly to prevent wear and handling damage (T73-P-1/700 engines), dated October 26, 1986. 
 
The following Modification Work Orders need not be incorporated for civil airworthiness certification: 
 
MWO 55-1500-204-30-1, MWO 55-1520-217-20-2, MWO 55-1520-217-20-3, 
MWO 55-1520-217-20-5, MWO 55-1520-217-30-21, MWO 55-1520-217-30-24,  
MWO 55-1520-217-30-26, MWO 55-1520-217-30-35, MWO 55-1520-217-30-40,  
MWO 55-1520-217-30-42, MWO 55-1520-217-30-49, MWO 55-1520-217-30-50, 
MWO 55-1520-217-30-64, MWO 55-1520-217-30-65, MWO 55-1520-217-30-66,  
MWO 55-1520-217-30-68, MWO 55-1520-217-40-2, MWO 55-1520-217-30-50-5,  
MWO 55-1680-200-20-2, MWO 55-1680-321-50-1, MWO 55-2835-203-30-1, 
MWO 55-2835-204-50-1, MWO 55-2835-204-50-2, MWO 55-2835-204-50-3, 
MWO 55-2835-204-50-4, MWO 55-2835-204-50-5, MWO 55-2835-204-50-6 
MWO 55-1615-237-55-1. 
 
In order to be eligible for civil airworthiness certification, the rotorcraft must be equipped with a Sikorsky  
P/N 6435-20400-058 (heavy duty) main gearbox assembly.   
 
The installation of a Department of the Army cargo pod will require further FAA approval.

H40NM 6 
NOTE 7.   Prior to civil airworthiness certification,  compliance with the following must be accomplished: 
 
 Department of the Army Technical Bulletins: 
 TB 1-1520-217-20-36, Vertical Hinge Pi ns, CH-54A, dated January 28, 1992. 
 
 All other Technical Bulletins have been incorporated in to the current Department of the Army Maintenance  
 Manuals (See NOTE 8). 
 
 Federal Aviation Administration (FAA) Airworthiness Directive (AD) Nos.: 
 
 71-24-05  JFTD12A Engine Compressor Rotor Disc 
 74-16-05       Main Rotor Head 
 76-06-01       Hydraulic Pumps 
 77-20-01       Main Transmission Plates (see exception, below) 
 85-18-01       Main Rotor Blade Outboard Spars 
 85-25-03       Torque Tube Inner Bracket Assy. 
 90-26-12       Main Rotor Blades (see additional requirement) 
 
 AD 75-11-11 is not applicable. 
 
  The following exception to AD 77-20-01 applies to all CH-54A helicopter serial numbers listed herein:  
  (1) Aircraft certified under this data sheet will not be  operated in high-cycle operations until compliance with  
   AD 77-20-01 has been accomplished (reference AD 90-26-12 for definition of high cycle). 
  (2)   Until compliance with AD 77-20-01, aircraft are to be  inspected daily for magnesium chips in the oil screen  
   in accordance with S/B 64B35-7A. 
  (3)   Until compliance with AD 77-20-01, MGB must have  boroscope inspection of planetary plate in accordance  
   with S/B 64B35-7A within 50 hours of the formal FAA screening inspection, and at 50 hour intervals  
   thereafter, until planetary plate is replaced. 
 
 If main rotor blades part number 6415-20201-041 or -042 are used, the BIM inspections of AD 90-26-12 apply. 
   
NOTE 8. These helicopters must be serviced and maintained in compliance with the following Department of the Army  
 Technical Manuals (TM): 
 
TM 1-1500-328-23, "Aeronautical Equipment Maintenance Management Policies and Procedures," dated 
February 28, 1991. 
TM 11-6140-203-14-2, "Technical Manual Operators, Organizational, Direct Support, General Support, 
Maintenance Manual for Aircraft Nickel-Cadmium Batteries," with Change 1, dated December 28,1983.  
TM 11-1520-217-35, "Electrical Equipment Configuration," dated March 1967. 
TM 11-1520-217-PM, "Phased Maintenance Checklist," dated December 19, 1985, with Changes 1 and 2. 
TM 11-1520-217-PMD, "Preventive Maintenance Daily," dated July 10, 1984, with Change 1. 
TM 55-1520-217-23-1-1, "Aviation Unit and Intermediate Maintenance Manual," dated March 31, 1977, with 
Changes 1 through 21. 
TM 55-1520-217-23-1-2, "Aviation Unit and Intermediate Maintenance Manual," dated March 31, 1977, with 
Changes 1 through 11. 
TM 55-1520-217-23-1-3, "Aviation Unit and Intermediate Maintenance Manual," dated March 31, 1977, with 
Changes 1 through 8. 
TM 55-1520-217-23P-1, "Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List," dated 
November 14, 1979. 
TM 55-1520-217-23P-2, "Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List," dated 
November 14, 1979, with Change 1. 
TM 55-1520-217-23P-3, "Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List," dated 
November 14, 1979. 
TM 55-1520-217-23P-4, "Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List," dated 
November 14, 1979. 
TM 55-1520-217-MTF-1, "Maintenance Test Flight, CH-54A," dated June 17, 1985. 
TM 55-2835-203-23P, "Aviation Unit and Intermediate Maintenance Repair Parts and Special Tools List," dated 
December 15, 1980. 
TM 55-2835-204-24, "Maintenance Manual Auxiliary Power Unit," dated November 18, 1971, with  
Changes 1 through 4.

7 H40NM 
TM 55-2840-230-23P, "Aviation Unit and Intermediate Maintenance Repair parts and Special Tools List-Engine, 
Aircraft, Free Turbine T-73-P-1, T-73-P-700," dated November 30, 1977. 
TM 55-2840-230-24, "Maintenance Manual for T73-P-1 and T73-P-700," dated September 1, 1971, with  
Changes 1 through 6. 
 
NOTE 9. As stated in Pratt & Whitney engine Type Cer tificate Data Sheet No. E15EA-3, NOTE 13, the JFTD12A-4A 
 (commercial) and T73-P-1 (military) engines are identical .  When using the commercial version, maintenance  
 must be in accordance with the latest Pratt & Whitney commercial maintenance/overhaul manual. 
 
....END....
```

## ADs (1, in force first)

- [AD 2013-20-15](https://openairdocs.org/ad/2013-20-15): Tail Rotor Drive System · Erickson Air-Crane CH-54A. Effective Dec 5, 2013

## STCs approved under this data sheet (6)

- [STC SR00813SE](https://openairdocs.org/stc/SR00813SE): Fabrication and installation of Columbia Helicopters pylon fittings P/N C54S2022-1 and -2 for replacement of Sikorsky fittings P/N 6420-66341-101 and -102 at the transition of fuselage to the tail boom.. Columbia Helicopters Inc
- [STC SR00449SE](https://openairdocs.org/stc/SR00449SE): Replacement of oil in main transmission, intermediate gearbox and tail gearbox with Mobil SHC 627 synthetic bearing and gear lubricants. Columbia Helicopters Inc
- [STC SR00231SE](https://openairdocs.org/stc/SR00231SE): Relocation of the existing transmission oil cooler and blower, and a change in the oil cooler drive system from a belt drive to hydraulic motor drive.. Columbia Helicopters Inc
- [STC SR00316SE](https://openairdocs.org/stc/SR00316SE): Fabrication and installation of an externally mounted equipment shelf. Columbia Helicopters Inc
- [STC SR00282SE](https://openairdocs.org/stc/SR00282SE): Fabrication and installation of a fixed tail skid system to replace existing retractable tail skid system.. Columbia Helicopters Inc
- [STC SR00230SE](https://openairdocs.org/stc/SR00230SE): Fabrication and installation of an external cargo support beam, upper cargo hook and load cell system.. Columbia Helicopters Inc

---
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.