# TCDS R00003AC: Pickering Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Pickering Aviation Inc.
- Revision: 3
- Revised: April 2, 2026
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21
- Registered aircraft: 6, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/04/f1/04f1769cd6b93c8ff6f5c1550f7ff8c0dfbd0d109ce97178640dc3f1f15d0229
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID105755199020260504171829.0001
- Page: https://openairdocs.org/tcds/R00003AC

## Models (6)

As the data sheet lists them.

- EH-60A
- UH-60L
- UH-60A
- T700-GE-700
- T700-GE-701C
- T700-GE-701D/CC

## 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 8 9 
Rev. No. 3 3 3 3 3 3 3 3 3 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET R00003AC 
This data sheet, which is a part of Type Certificate No. R00003AC prescribes conditions and limitations under 
which the product for which the type certificate was issued meets the airworthiness requirements of the 14 Code of 
Federal Aviation Regulations (14 CFR). 
TYPE CERTIFICATE (TC) 
HOLDER:  
TYPE CERTIFICATE (TC) 
HOLDER RECORD:                N/A 
I – MODEL NUMBER: EH-60A (Restricted Category Military Rotorcraft) Approved May 13, 2019 
ENGINES: (2) General Electric T700-GE-700 Original 
(2) General Electric T700-GE-701C Alternate
(2) General Electric T700-GE-701D/CC Alternate
*See NOTE 9 for alternate engine information.
FUEL: Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1, or Jet B 
*See NOTE 16 for alternate and emergency fuels.
ENGINE LIMITS: (T700-GE-700) SHAFT HP POWER TURBINE RPM GAS GEN RPM POWER TURBINE INLET (TGT) 
Military Power (30 min.) 1,561 20,900 44,700 850º C 
Normal Cont. Cruise 1,318 20,900 44,700 775º C 
ENGINE LIMITS: (T700-GE-701C) SHAFT HP POWER TURBINE RPM / % GAS GEN RPM / % POWER TURBINE INLET (TGT) 
Contingency Rated Power (CRP) 
 (2 1/2 min. OEI) 1,940 20,900 / 100 44,700 / 102 903º C 
Maximum Rating (10 Min. dual) 1,890 20,900 / 100 44,700 / 102 878º C 
Intermediate Rated Power (IRP) 
(30 min dual) 1,800 20,900 / 100 44,700 / 102 851º C 
Maximum Continuous Power (MCP) 1,662 20,900 / 100 44,700 / 102 810º C 
R00003AC 
Pickering Aviation, Inc. 
EH-60A 
UH-60A 
UH-60L 
Revision: 3 
Date: January 24, 2025 
Pickering Aviation, Inc. 
3825 Market St. Suite# 121 
Denton, Texas 76209

Page 2 of 9 TCDS No. R00003AC 
ENGINE LIMITS: (T700-GE-701D/CC) SHAFT HP POWER TURBINE RPM / % GAS GEN RPM / % POWER TURBINE INLET (TGT) 
Contingency Rated Power (CRP) 
 (2 1/2 min. OEI) 1,940 20,900 / 100 44,700 / 102 903º C 
Maximum Rating (10 Min. dual) 1,890 20,900 / 100 44,700 / 102 878º C 
Intermediate Rated Power (IRP) 
(30 min dual) 1,800 20,900 / 100 44,700 / 102 851º C 
Maximum Continuous Power (MCP) 1,662 20,900 / 100 44,700 / 102 810º C 
TRANSMISSION LIMITS: TORQUE: 
110% Sin gle Engine (No Time Limit) 
100% Dual Engine (No Time Limit) *See NOTE 1 7 
ROTOR LIMITS: POWER OFF: 
Max. 26 5 RPM (110%) 
Min. 217 RPM (90%)   
 POWER ON: 
 Max. 
258 RPM (107%)  
Min. 219
 RPM (91%) 
AIRS
PEED LIMITS: Vne POWER ON:  
193 knots IAS, (221 MPH). 
Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft 
Model EH -60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or 
later FAA approved revisions, for variations of Vne with gross weight, pressure 
altitude, and 
temperature. 
Refer 
to PA-1-1 520-237 -10, Operator’s Manual for the Restricted Category Aircraft 
Model EH -60A, UH-6 0A, UH-6 0L  Helicopter Rev. 3.0, Dated September 06, 2024, or 
later FAA a pproved revisions, for additional limitation data. 
C.G
. RANGE:
EMPTY WEIGHT C.G. RANGE: 
DATUM: 
LEVELING MEANS: 
None. 
341.2 inches forward of the ma in rotor c entroid. 
 Plumb bob in L/H cabin door frame to leveling plate on cabin floor or electronic leveling 
means 
in accordance with PA-1-1520-237-10, Operator’s Manual for the Restricted Category 
Aircraft Model EH-6 0A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 
2024, or later FAA approved revisions. 
C.G.RANGE
AIRCRAFT
WEIGHT LBS
INCHES AFT OF DATUM
347.7 360.2
22,000
13,400
13,050
366.3
11,500
358.1342.6
345.5
13,700
15,900

Page 3 of 9 TCDS No. R00003AC 
MAXIMUM WEIGHT: 22,000 lbs. *See NOTE 15 
MINIMUM CREW: 2 (Pilot in Command and Second in Command) both located at aircraft station 227.1. 
*See NOTE 14
NUMBER OF SEATS:  OEM established locations: 2 at Sta. 227.1; 2 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 4 
at Sta. 387.2. No Passengers permitted. *See NOTE 11 
MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E 
Sta. 247 to Sta. 288 
5460 lbs. 
Sta. 288 to Sta. 343 
8370 lbs. 
Sta. 343 to Sta. 398 
8370 lbs. 
FUE
L CAPACITY: 
OIL CAPACITY: 
OTHER LIMITS: 
Main Tanks usable U.S. Gallons of fuel are: 360 (gravity), 359 (pressure), and 356 (closed 
circuit). 
7 quarts each engine at STA. 375.0 
 Refer to PA-1-1520-237-10, Operator’s Manual for the R estricted Category Aircraft 
Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0,  Dated September 06, 2024, or 
later FAA approved revisions. 
Reference the Note Section for additional limitations. 
II – MODEL NUMBER: UH-60A (Restricted Category Military Rotorcraft) Approved February 11, 2021 
ENGINES: (2) General Electric T700-GE-700 Original 
 (2) General Electric T700-GE-701C Alternate
(2) General Electric T700-GE-701D/CC Alternate
 *See NOTE 9 for alternate engine information.
FUEL: Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1, or Jet B 
*See NOTE 16 for alternate and emergency fuels.
ENGINE LIMITS: (T700-GE-700) SHAFT HP POWER TURBINE RPM GAS GEN RPM POWER TURBINE INLET (TGT) 
Military Power (30 min.) 1,561 20,900 44,700 850º C 
Normal Cont. Cruise 1,318 20,900 44,700 775 º C 
ENGINE LIMITS: (T700-GE-701C) SHAFT HP POWER TURBINE RPM / % GAS GEN RPM / % POWER TURBINE INLET (TGT) 
Contingency Rated Power (CRP) 
 (2 1/2 min. OEI) 1,940 20,900 / 100 44,700 / 102 903º C 
Maximum Rating (10 Min. dual) 1,890 20,900 / 100 44,700 / 102 878º C 
Intermediate Rated Power (IRP) 
(30 min dual) 1,800 20,900 / 100 44,700 / 102 851º C 
Maximum Continuous Power (MCP) 1,662 20,900 / 100 44,700 / 102 810º C 
EN
GINE LIMITS: (T700-GE-701D/CC) SHAFT HP POWER TURBINE RPM / % GAS GEN RPM / % POWER TURBINE INLET (TGT) 
Contingency Rated Power (CRP) 
 (2 1/2 min. OEI) 1,940 20,900 / 100 44,700 / 102 903º C

Page 4 of 9 TCDS No. R00003AC 
Maximum Rating (10 Min. dual) 1,890 20,900 / 100 44,700 / 102 878º C 
Intermediate Rated Power (IRP) 
(30 min dual) 1,800 20,900 / 100 44,700 / 102 851º C 
Maximum Continuous Power (MCP) 1,662 20,900 / 100 44,700 / 102 810º C 
TRANSMISSION LIMITS: TORQUE:  
110% Sin gle Engine (No Time Limit) 
100% Dual Engine (No Time Limit) *See NOTE 17 
ROTOR LIMITS: POWER OFF: 
Max. 265 RPM (110%) 
Min. 217 RPM (90%)   
 POWER ON: 
 Max.
 258 RPM (107%)  
Min. 2
19 RPM (91%) 
AIR
SPEED LIMITS: Vne POWER  ON:  
193 knots IAS, (221 MPH). 
Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft 
Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or 
later FAA approved revisions, for v ariations of Vne with gross weig ht, p ressure 
altitude, and temper ature. 
Refer to PA-1-1 520-237-10, Operator’s Manual f or th e Restricted C ategory Aircraft 
Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3. 0, Dated September 06, 2024, or 
later FAA a pproved revisions, for additional limitation data. 
C
.G. RANGE:
EMPTY
 WEIGHT C.G. RANGE: 
DATUM: 
LEVELING MEANS: 
MAXIMUM WEIGHT: 
MINIMUM CREW: 
None. 
341.2 inches forward of the main rotor centroid. 
 Plumb bob in L/H cabin door frame to leveling plate on cabin floor or electronic leveling 
means in accordance with PA-1-1520-237-10, Operator’s Manual for the Restricted 
Category Aircraft Model EH-6 0A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0 , Dated 
September 06, 2024 or l ater FAA approved rev isions. 
22,000 lbs. *See NOTE 15 
2 (Pilot in Command and Second in Command) both located at aircraft station 227.1. 
*See NOTE 14
C.G.RANGE
AIRCRAFT
WEIGHT LBS
INCHES AFT OF DATUM
347.7 360.2
22,000
13,400
13,050
366.3
11,500
358.1342.6
345.5
13,700
15,900

Page 5 of 9 TCDS No. R00003AC 
NUMBER OF SEATS:  OEM established locations: 2 at Sta. 227.1; 2 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 
4 at Sta. 387.2. No Passengers permitted. *See NOTE 11 
MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E 
Sta. 247 to Sta. 288 
5460 lbs. 
Sta. 288 to Sta. 343 
8370 lbs. 
Sta. 343 to Sta. 398 
8370 lbs. 
FUEL CAPAC
ITY: 
OIL CAPACITY: 
OTHER LIMITS: 
Main Tanks usable U.S. Gallons of fuel are: 360 (gravity), 359 (pressure), and 356 (closed 
cir
cuit). 
7 quarts each engine at STA. 375.0 
Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft 
Model EH-60A, UH-60A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or 
later FAA approved revisions. 
Reference the Note Se ction f or additional limitations. 
FUEL: 
III – MODEL NUMBER: UH-60L (Restricted Category Military Rotorcraft) Approved January 24, 2025 
ENGINES: (2) General Electric T700-GE-701C Original
(2) General Electric T700-GE -701D/CC Alternate
*See NOTE 9 for al ternate engine information.
Aviation Kerosene JP-4, JP-5, JP-8, Jet A, Jet A-1, or Jet B 
*See NOTE
 16 for alternate and emergency fuels.
ENGINE LIMITS: (T700-GE-701C) SHAFT HP POWER TURBINE RPM / % GAS GEN RPM / % POWER TURBINE INLET (TGT) 
Contingency Rated Power (CRP) 
 (2 1/2 min. OEI) 1,940 20,900 / 100 44,700 / 102 903º C 
Maximum Rating (10 Min. dual) 1,890 20,900 / 100 44,700 / 102 878º C 
Intermediate Rated Power (IRP) 
(30 min dual) 1,800 20,900 / 100 44,700 / 102 851º C 
Maximum Continuous Power (MCP) 1,662 20,900 / 100 44,700 / 102 810º C 
ENGINE
 LIMITS: (T700-GE-701D/CC) SHAFT HP POWER TURBINE RPM / % GAS GEN RPM / % POWER TURBINE INLET (TGT) 
Contingency Rated Power (CRP) 
 (2 1/2 min. OEI) 1,940 20,900 / 100 44,700 / 102 903º C 
Maximum Rating (10 Min. dual) 1,890 20,900 / 100 44,700 / 102 878º C 
Intermediate Rated Power (IRP) 
(30 min dual) 1,800 20,900 / 100 44,700 / 102 851º C 
Maximum Continuous Power (MCP) 1,662 20,900 / 100 44,700 / 102 810º C

Page 6 of 9 TCDS No. R00003AC 
TRANSMISSION LIMITS: TORQUE:  
135% Single Engine (No Time Limit) 
120% Dual Engine; 80 KIAS or below (No Time Limit) 
100% Dual Engine; Above 80 KIAS (No Time Limit) *See NOTE 17 
ROTOR LIM
ITS: POWER OFF: 
Max.  265 RPM (110%) 
Min. 217 RPM (90%)   
 POWER ON: 
 Max. 258 RPM (107%)  
Min. 2
19 RPM (91%) 
AIR
SPEED LIMITS: Vne POWE R ON:  
193 knots IAS, (221 MPH). 
Refer to PA-1-1 520-237-10, Operator’s Manual for the Restricted Category Aircraft 
Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or 
later FAA approved revisions, for variations of Vne with gross weight, pressure 
altitude, and temperatur e. 
Refer to PA-1-1 520-237-10, Operator’s Manual fo r th e Restricted Catego ry Aircraft 
Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated September 06, 2024, or 
later FAA approved  revisions, for additional limitation data. 
C.G. R
ANGE:
EMP
TY WEIGHT C.G. RANGE: 
DATUM: 
LEVELING MEANS: 
MAXIMUM WEIGHT: 
MINIMUM CREW: 
NUMBER OF SEATS: 
None. 
341.2 inches forward of the main rotor centroid. 
 Plumb bob in L/H cabin door frame to leveling plate on cabin flo or or electronic leveling 
means in accordance with accordance with  PA -1-1520-237-10, Operator’s Manual for the 
Restricted Category Aircraft Model EH-6 0A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated 
September 06, 2024, or later FAA approved revisions.  
22,000 lbs. *See NOTE 15 
2 (Pilot in Command and Second in Command) both located at aircraft station 227.1. 
*See NOTE 14
 OEM established locations: 2 at Sta. 227.1; 2 at Sta. 282.0; 3 at Sta. 320.7; 4 at Sta. 339.8; 
4 at Sta. 387.2. No Passengers permitted. *See NOTE 11 
MAX COMPARTMENT WEIGHT: Compartment C Compartment D Compartment E 
Sta. 247 to Sta. 288 
5460 lbs. 
Sta. 288 to Sta. 343 
8370 lbs. 
Sta. 343 to Sta. 398 
8370 lbs. 
C.G.RANGE
AIRCRAFT
WEIGHT LBS
INCHES AFT OF DATUM
347.7 360.2
22,000
13,400
13,050
366.3
11,500
358.1342.6
345.5
13,700
15,900

Page 7 of 9 TCDS No. R00003AC 
FUEL CAPACITY: 
OIL CAPACITY: 
OTHER LIMITS: 
Main Tanks usable U.S. Gallons of fuel are: 360 (gravity), 359 (pressure), and 356 (closed 
circuit). 
7 quarts each engine at STA. 375.0 
Refer to PA-1-1 520-237-10, Operator’s Manual for the Restr icted Category Aircraft 
Model EH-60A, UH-6 0A, UH-6 0L Helicopter Rev. 3.0, Dated  September 06, 2024, or 
later FAA a pproved revisions. 
Reference the Note Section for additional limitations. 
DATA PERTINENT TO ALL MODELS 
SERIAL NO. APPROVED:  Refer to the latest FAA approved revision of  Pickering Aviation, Inc. Document No. PA-03 
Approved Serial Numbers List  for the listing of all EH-60A, UH-60A, and UH-60L serial 
numbers that are approved by the FAA to be conformed under this Restricted Category Type 
Certificate.  
CERTIFICATION BASIS:  Title 14 CFR p art 21 §21.25(a)(2) effective February 1, 1965, including Amendments 21-1 
through 21-42 for the special purposes listed in 14 CFR §21.25 (b)(1)(2)(7). 
§ 21.25(b)(1) Agriculture Operations
§ 21.
25(b)(2) Forest & Wildlife Conservation
§ 21.25(b)(7) External Loads
EQUI
PMENT: 
NO
TE SECTION 
NOTE 1: 
NOTE 2: 
In accordance with 14 CFR §36.1(a)(4), compliance with the noise requirements as not 
sh
own. Therefore, in accordance with section 36.1(a)(4), aircraft certificated under this Type 
Certificate are only eligible for (1) agricultu ral operations as defined in § 137.3; (2) aerial 
dispensing of liquids and firefighting  materials; and (3) external loads as defined in § 
133.1(b). 
Any a lteration to the aircraft f o r  S pecial P urpose operations not i de ntifie d above requires 
further FAA approval an d in addition, m ay require noi se a nd/or flight testing. 
This aircraft is approved for D ay or N i ght V F R o perations only.  Flight i nt o  known icing 
conditions is prohibited. 
Any subsequent modifications to the helicopters type certified under this Type C ertificate are 
to have the certification basis for that modification established under 14 CFR §21.101. 
Ot
herwise, non-significant modifications are to meet the requirements of 14 CFR  part  29 
a
irworthiness standards, transport category rotorcraft and 14 CFR §29.1529, Instructions for 
C
ontinued Airworthiness. 
 The basic required equipment neces sary for t he particular special purpose ope ration m ust be 
installed for ce rtification. 
 A current weight and balance report including a list of equipment included in the certified 
empty 
weight and loading instructions (when necessary), must  be provided for each helicopter 
a
t the time of original airworthiness certification. 
The following placards must be prominently displayed in the coc kpit in full view of the pilots: 
P
LACARD NO. 1 
THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING 
LIMITATIONS SPECIFIED IN THE AP PROVED HELICOPTER OP ERATIONS 
MANUAL.

Page 8 of 9 TCDS No. R00003AC 
PLACARD NO. 2 
NOTE 3
: 
NOTE 4: 
NOTE 5: 
NOTE 6: 
THIS HELICOPTER MUST BE OPERATED IN ACCORDANCE WITH THE  
RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR PART 91.313  OR 
PART 133 FOR EXTERNAL LOAD OPERATIONS. 
PLACARD NO. 3 
EXTERNAL L OADS OP ERATIONS: VNE W ILL BE DE TERMINED FOR E ACH 
PROPOSED EXTERNAL LOAD APPLICATION. 
PLACARD NO. 4 
THIS AI RCRAFT I S APPROVED FOR DAY OR NIGHT VF R OP ERATIONS ONL Y. 
FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED. 
 The helicopter(s) mu st be serviced, maintain ed, inspected, repaired, and overhauled in 
accordance with the requirements specified in Pickering Aviation, Inc. Document no. PA-04 
Instructions for Continued Airworthiness Rev. 5.0, Dated December 19, 2024, or later 
FAA approved revisions, or inspected in accordan ce with other FAA approved 
inspection programs. The service life limited parts overhaul and retirement intervals for these 
helicopters are specified in Pickering Aviation, Inc. Document no. PA-04 Instructions for 
Continued Airworthiness Rev. 5.0, Dated December 19, 2024, o r later FAA approved 
revisions. The latest FAA approved ICA must be provided with each helicopter at delivery 
and all later FAA approved revisions must be provided to the helicopter owner and operator. 
 The TC Holder’s data plate required  by 14 CFR §45.13 must be installed in ac cordance with 
Pickering Aviation, Inc. Data Plate Drawing No. PA-H60-DP Rev. 1, Dated June 13, 2022, 
or later FAA approved revisions. 
 The helicopter(s) must be operated in accordance with the Operator Manual comprised of the 
following: 
PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-6 0A, 
UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, o r later FAA 
approved revisions. 
Prior to obtaining an original Airworthiness Certificate: 
A. Each h
elicopter must pass a conformity inspection in accordance with Pickering Aviation,
Inc. Document no. PA-ACR, Aircraft Configuration Report, Rev. 1, Dated June 13, 2023,
or later revisions.
B. Each helicopter must complete t he Aircraft Configuration Report, Document no. PA -
ACR, Rev. 1, Dated June 13, 2023, or later revisions. The ACR provides evidence of the
aircraft’s critical historical records, at the time of TC conformity, to show it is safe for its
attended use.
C. Each helicopter must pass an inspection for any possible hidden damage and the Military
records reviewed for acceptability of any repairs or alterations.
D. The maintenance, overhaul, and modification records of each helicopter must be reviewed
for military changes that may affect the airworthiness of the helicopter. Modifications and 
changes of equipment that affect the safety or performance of the helicopter must be
approved by the FAA.
E. After the required inspections, the aircraft must be found to be in a good state of
preservation, repair, and in a condition for safe operation.
NOTE 7:  Restricted Category helicopter may not be operated in a foreign country without the expre ss 
written approval of that country’s Civil Air Authority. 
NOTE 8:  This helicopter has not been shown to meet the requirements of the applicable comprehensive 
and detailed airworthiness code as provided by Annex 8 to the  Convention on International 
Civil Aviation.

Page 9 of 9 TCDS No. R00003AC 
NOTE 9: 
NOTE 10: 
NOTE 11: 
NOTE 12: 
NOTE 13: 
NOTE 14: 
NOTE 15:  
NOTE 16:  
NOTE 17: 
The alternate engines T700-GE-701C and/or T700-GE-701D/CC were approved in 
accordance with Order 8110.56B, para 4-15, as modifications “previously qualified by 
the U.S. Armed Forces.”  Installation of the approved alternate engines must be in 
accordance with MWO 1-1520-237-20-3. T700-GE-701C and T700-GE-701D/CC 
performance information and limitations are contained in Chapter 7A of 
PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model 
EH-60A, UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, or later 
FAA approved revisions. 
All applicable FAA ADs and Military Safety Messages listed in Pickering Aviation, 
Inc. Document no. PA-ACR, Aircraft Configuration Report, Rev. 1, Dated: June 13, 2023, 
or later revisions, must be complied with prior to original airworthiness cer tification.  
 No person may be carried on board this aircraft unless th at person is a flight crewmember; 
is a flight crewmember trainee, performs an essential function in connection with a 
special purpose operation for which the aircraft is certificated,  or is necessary to accomplish 
the work activity directly associated with that special purpose. Reference 
14 CFR §91.313(d)(1)(2)(3)(4).
 Any alteration to the typ e design of this aircr aft may require FAA approved Instructions 
for Continued Airworthiness. These instructions must be submitted and accepted 
by the Administrator, prior to appr oval for return to service. 
The established life limits for the products and articles of the Pickering Aviation, Inc. 
EH-60A, UH-60A, and UH-60L are based on the satisfactory service history as 
designed and operated by  the US Armed Forces.  
Therefore, it is mandatory to constantly track and comply with the current life limits of 
certain critical components as identified in the FAA approved Airworthiness Limitation 
Section of Pickering Aviation, Inc. Instructio ns for Continued Airworthiness Document no. 
PA-04, Rev. 5.0, Dated Decemebr 19, 2024, or later FAA approved revisions. 
Pilot in Command and Second in Command rating requirements: 
Pilot in Command must comply with 14 CFR § 61.31 
Second in Command must comply with 14 CFR § 61.55. 
EH-60A, UH-60A, and UH-60L maximum gross weight can be exten ded from 
20,250 pounds to 22,000 pounds only when wedge mounted pitot-static probes and either/or 
MWO 55-1520-237-50-58 or MWO 1-1520-237-50-73 are installed.
Alternative and emergency fuels are listed in PA-1-1520-237-10, Operator’s Manual 
for the Restricted Category Aircraft Model EH-60A, UH-60A, UH-60L Helicopter 
Rev. 3.0, Dated September 06, 2024, or later FAA approved revisions. 
Helicopters prior to S/N 91−26354 that are not equipped with improved main rotor flight 
controls are further restricted above 80 KIAS to Dual−Engine Continuous Torque Limits as 
indicated by a placard on the instrument panel. Refer to figure 5−3 for placard “Dual- 
Engine Torque Limitations at Airspeeds Above 80 KIAS 701C - 701D/CC” of 
PA-1-1520-237-10, Operator’s Manual for the Restricted Category Aircraft Model EH-60A, 
UH-60A, UH-60L Helicopter Rev. 3.0, Dated September 06, 2024, or later FAA approved 
revisions.
– END  –
```

## ADs

None name its models.

## Registered aircraft by registry model (OpenAirDocs)

- [Pickering UH-60A](https://openairdocs.org/model/pickering-uh-60a): 4 aircraft (registry code 8141920)
- [Pickering UH-60L](https://openairdocs.org/model/pickering-uh-60l): 2 aircraft (registry code 8141925)
- [Pickering EH-60A](https://openairdocs.org/model/pickering-eh-60a): 0 aircraft (registry code 8141901)

## STCs approved under this data sheet (28)

- [STC SR02753LA](https://openairdocs.org/stc/SR02753LA): Installation of an engine Inlet Barrier Filter (IBF). Aerometals Inc.
- [STC SR02597SE](https://openairdocs.org/stc/SR02597SE): Installation of Purge Fuel Collector System. Timberline Aerospace LLC
- [STC SR02650SE](https://openairdocs.org/stc/SR02650SE): Installation of Station 34.5 Beam Modification. Timberline Aerospace LLC
- [STC SR12058AK](https://openairdocs.org/stc/SR12058AK): Installation of Recoil Aerospace, Inc. T750-I Internal Fire Suppression Tank. Recoil Aerospace Inc.
- [STC SR12471AT](https://openairdocs.org/stc/SR12471AT): Installation of RMCI Health Useage and Monitoring System (HUMS). RMCI Inc.
- [STC SR00903DE](https://openairdocs.org/stc/SR00903DE): Installation of Left and Right, Hand Hold, Step and Step Fairing modification. Blackhawk Mission Equipment
- [STC SR12380LA](https://openairdocs.org/stc/SR12380LA): Installation of Aerocraft's External Load Mount Kit (ARC-H60ELM). Aerocraft Incorporated
- [STC SR01099DE](https://openairdocs.org/stc/SR01099DE): Installation of the GPMS Foresight MX Condition Monitoring System. GPMS International Inc.
- [STC SR04461CH](https://openairdocs.org/stc/SR04461CH): Installation of a Helitak FT4500 Black Hawk Fire Tank Liquid Dispensing System. Helitak USA, LLC
- [STC SR04527AT](https://openairdocs.org/stc/SR04527AT): Installation of Robertson Fuel System 200 Gallon Internal Auxilliary Fuel Tank System (IAFTS. Ace Aeronautics, LLC
- [STC SR02794LA](https://openairdocs.org/stc/SR02794LA): Installation of Ballast Box. Aerocraft Incorporated
- [STC SR02767LA](https://openairdocs.org/stc/SR02767LA): Installation of H-60 Electric APU Starter Modification to replace the original equipment hydraulic APU starter system on Restricted Category H-60 Firefighting and Utility Helicopters. Aerocraft Inc.
- [STC SR02764LA](https://openairdocs.org/stc/SR02764LA): Installation of lift kit. Aerocraft Incorporated
- [STC SR02544LA](https://openairdocs.org/stc/SR02544LA): Installation of a left side bubble window and a modified left side main landing gear fairing. Aerocraft Incorporated
- [STC SR02744SE](https://openairdocs.org/stc/SR02744SE): Installation of BLR FastFin System. BLR Aerosapce LLC
- [STC SR01944WI](https://openairdocs.org/stc/SR01944WI): Installation of the G5000H Integrated Flight Deck with Synthetic Vision. Ace Aeronautics LLC
- [STC SR00919DE](https://openairdocs.org/stc/SR00919DE): Installation of Left and Right Pulse Light. Blackhawk Mission Equipment
- [STC SR02584AK](https://openairdocs.org/stc/SR02584AK): Installation of Recoil Aerospace, Inc. T1000-E or T650-E Fire Suppression Tank. Recoil Aerospace Inc.
- [STC SR11809SE](https://openairdocs.org/stc/SR11809SE): Installation of pilot and Co-Pilot Restraint Systems. Timberline Aerospace
- [STC SR02688SE](https://openairdocs.org/stc/SR02688SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SR04618CH](https://openairdocs.org/stc/SR04618CH): Installation of Luma Technologies LT-4082 and LT-4106 series 82 and 106 Station Integration LED Display Panels with LT-2205 and LT-2206 series 5 and 6 Station LED Display/Reset Panels. Luma Technologies LLC
- [STC SR00922DE](https://openairdocs.org/stc/SR00922DE): Relocation and installation of Lead-Acid batteries, P/N RG24-15, in replacement of aircraft main batteries. Blackhawk Mission Equipment
- [STC SR02698SE](https://openairdocs.org/stc/SR02698SE): Installation of Onboard Systems International Cargo Hook Kits. Onboard Systems International
- [STC SR02743SE](https://openairdocs.org/stc/SR02743SE): Installation of folding crew step and modification of fairing. Timberline Aerospace LLC
- [STC SR02760LA](https://openairdocs.org/stc/SR02760LA): Installation of Aerocraft Incorporated H-60 Blackhawk Helicopter Cargo Basket. Aerocraft Inc
- [STC SR02657SE](https://openairdocs.org/stc/SR02657SE): Installation of Model 370i Fire Attack System. Simplex Manufacturing Company
- [STC SR02617SE](https://openairdocs.org/stc/SR02617SE): Installation of a Mechanical Specialties Model 909 Cargo Hook. Mechanical Specialties Inc
- [STC SR00896DE](https://openairdocs.org/stc/SR00896DE) (historical): The installation of a bubble window with view port as a direct replacement for the existing window in the left hand side
Cockpit door. Blackhawk Mission Equipment

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