15798 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 

■ 36. In § 147.52, a new paragraph (c) is 

added to read as follows: 

§ 147.52 Approved tests. 

* * * * * 

(c) The following diagnostic test kits 

that are not licensed by the Service (e.g., 

bacteriological culturing kits) are 

approved for use in the NPIP: 

(1) Rapid Chek©Select TMSalmonella 

Test Kit, Strategic Diagnostics, Inc., 

Newark, DE 19713. 

(2) ADIAFOOD Rapid Pathogen 

Detection System for Salmonella spp., 

AES Chemunex Canada. Laval, QC 

(Canada) H7L4S3. 

(3) DuPont Qualicon BAX Polymerase 

Chain Reaction (PCR)-based assay for 

Salmonella, DuPont Qualicon, 

Wilmington, DE 19810. 

Done in Washington, DC, this 16th day of 

March 2011. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2011–6539 Filed 3–21–11; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. NM428; Special Condition No. 

25–417–SC] 

Special Conditions: Boeing 747–468, 

Installation of a Medical Lift 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Boeing 747–468 airplane. 

This airplane, as modified by Jet 

Aviation, will have a novel or unusual 

design feature associated with the 

installation of a medical lift. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These special conditions contain the 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

DATES: Effective Date: March 22, 2011. 

FOR FURTHER INFORMATION CONTACT: 

Jayson Claar, Transport Airplane 

Directorate, Aircraft Certification 

Service, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; 

telephone (425) 227–2194; fax (425) 

227–1149; e-mail jayson.claar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On March 2, 2007, Jet Aviation 

Engineering Services L.P. (JAES), of 

Teterboro, New Jersey, applied for a 

supplemental type certificate for a 

reconfiguration of an aircraft interior in 

a 747–468. The Boeing Model 747–468 

airplane is FAA approved under Type 

Certificate A20WE as a large transportcategory airplane that is limited to 660 

passengers or fewer, depending on the 

interior configuration. 

This modification includes the 

installation of a medical lift between the 

main deck and upper deck. The lift 

allows the transport of a single occupant 

between the decks during cruise or 

ramp operations. The applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for this design feature. 

Type Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.101, 

JAES must show that the 747–468, as 

changed, continues to meet the 

applicable provisions of the regulations 

incorporated by reference in Type 

Certificate A20WE, or of the applicable 

regulations in effect on the date of 

application for the change. The 

regulations incorporated by reference in 

the type certificate are commonly 

referred to as the ‘‘original typecertification basis.’’ The regulations 

incorporated by reference in Type 

Certificate A20WE are as follows: 

• Part 36, as amended by 

Amendments 36–1 through 36–15, and 

any later amendments in existence at 

the time of certification. 

• Special Federal Aviation Regulation 

(SFAR) 27, as amended by Amendments 

27–1 through 27–6 and any later 

amendments in existence at the time of 

type certification. 

• Part 25, effective February 1, 1965, 

as amended by Amendments 25–1 

through 25–59, and the part 25 sectionnumber exceptions itemized in Type 

Certificate A20WE. 

The following special conditions, 

exemptions, and equivalent safety 

findings, which are part of the Model 

747–300 certification basis, are also part 

of the certification basis for the Model 

747–400. 

The special conditions include those 

enclosed with an FAA letter to The 

Boeing Company dated February 20, 

1970, and the following: 

1. Special Condition 4A, revised to 

apply to airplanes with the landing-gear 

load-evener system deleted, was 

recorded as an enclosure to an FAA 

letter to The Boeing Company dated 

May 12, 1971. 

2. Special Condition No. 25–61–NW– 

1, for occupancy not to exceed 32 

passengers on the upper deck of 

airplanes with a spiral staircase, was 

transmitted to The Boeing Company by 

FAA letter dated February 26, 1975. 

3. Special Condition No. 25–71–NW– 

3, for occupancy not to exceed 45 

passengers on the upper deck of 

airplanes with a straight-segmented 

stairway, was transmitted to The Boeing 

Company by FAA letter dated 

September 8, 1976. 

4. Modification of Special Condition 

No. 25–71–NW–3, for occupancy not to 

exceed 110 passengers on the upper 

deck of airplanes with a straightsegmented stairway, was transmitted to 

The Boeing Company by FAA letter 

dated August 3, 1981. 

5. Special Condition No. 25–77–NW– 

4, modification of the autopilot system 

to approve the airplane for use of the 

system under Category IIIb landing 

conditions, was transmitted to The 

Boeing Company by FAA letter dated 

July 8, 1977. 

6. Special Condition No. 25–ANM–16, 

for use of an overhead crew-rest area, 

occupancy not to exceed ten 

crewmembers, was transmitted to The 

Boeing Company by FAA letter dated 

November 19, 1987. The FAA-approved 

procedures required for compliance 

with paragraph 13 of the special 

condition are located in Boeing 

Document D926U303, Appendix D. 

7. Special Condition no. 25–ANM–24, 

applicable to flight-deck displays and 

propulsion-control systems, was 

provided to Boeing on December 22, 

1988. 

8. Special Condition No. 25–ANM–25, 

which established lightning- and radiofrequency-energy protection 

requirements, was provided to Boeing 

on December 22, 1988. 

Exemptions From Part 25 

Exemption no. 1013A, dated 

December 24, 1969: Exemption from 

Section 25.471(b) to allow lateral 

displacement of the center of gravity 

from the airplane centerline. 

The following optional requirements, 

which are part of the Model 747–300 

certification basis, apply also to the 

747–400: 

TABLE 1—OPTIONAL REQUIREMENTS

Requirement Section 

Ditching provisions ............. 25 .801 

Ice-protection provisions ..... 25 .1419 

The following equivalent-safety 

findings, previously made for earlier 

models under the provisions of 


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Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 15799 

§ 21.21(b)(1), are also applicable to the 

Model 747–400: 

TABLE 2—EQUIVALENT-SAFETY FINDINGS

Requirement Section 

Width of aisle ......................................................................................................................................................... 25.815. 

Pilot-compartment view ......................................................................................................................................... 25.773. 

Use of 1-g stall speed (nonstructural items) ......................................................................................................... Several (747–400 only). 

Use of 1-g stall speed (structural items) ............................................................................................................... Several (747–400 only). 

Position-light distribution and intensities ............................................................................................................... 25.1389(b)(3) (747–400 only). 

Fire-detection system ............................................................................................................................................ 25.1203.1

Pressure relief ........................................................................................................................................................ 25.1103(d).1

Emergency-locator transmitter (ELT) .................................................................................................................... 25.1415(d). 

Emergency-exit marking ........................................................................................................................................ 25.811(f). 

1Applies to RB211–524G/H series engine installations only. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the 747–468 because of a novel or 

unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the 747–468 must comply 

with the fuel-vent and exhaust-emission 

requirements of 14 CFR part 34, and the 

noise certification requirements of 14 

CFR part 36. 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.101. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the applicant apply 

for a supplemental type certificate to 

modify any other model included on the 

same type certificate to incorporate the 

same or similar novel or unusual design 

feature, the special conditions would 

also apply to the other model under 

§ 21.101. 

Novel or Unusual Design Features 

The original aircraft configuration 

included a straight stairway between the 

main deck and upper deck at Fuselage 

Station 870. The stairway is relocated in 

the new configuration, and the existing 

stairway is replaced with an electrically 

powered medical lift using the opening 

in the upper deck formerly occupied by 

the stairs. When the lift is not in 

operation, the upper-deck opening is 

covered by floor panels. These floor 

panels are opened up prior to operation 

of the lift and form a protective fencing 

around the upper-deck opening. 

The purpose of the medical lift is to 

move an occupant between the master 

lounge in the upper deck and the 

medical room on the lower deck. 

The lift platform is driven by two 

redundant electrical motors, mounted to 

the rear wall, between the struts. A 

lifting gear-drive with shafts and gear 

boxes is powered on the front and rear 

of the lift platform. The spindles are 

supported at the lifting gear on the 

lower support structure and with a strut 

support on the upper deck. The lift 

platform is guided in lateral directions 

with the guiding rails mounted on the 

struts. 

Discussion 

Due to the novel or unusual features 

associated with the installation of this 

medical lift, the following special 

conditions are considered necessary to 

provide a level of safety equal to that 

established by the airworthiness 

regulations incorporated by reference in 

the type-certificate. 

Discussion of Comments 

Notice of proposed special conditions 

no. 25–99–11–SC for the Boeing Model 

747–468 airplane was published in the 

Federal Register on May 18, 2010 (75 

FR 27662). No public comments were 

received and the special conditions are 

adopted as proposed. 

After the public-comment deadline on 

June 17, 2010, the FAA added text 

referenced in Note 1 in Table 2, and 

added special conditions 14e and f, and 

additional text to special condition 15a. 

The FAA has determined that this 

additional information enhances, and 

does not compromise, safety; does not 

materially affect the intent of the special 

conditions upon which the pubic had 

opportunity to comment; and therefore 

does not warrant a second publiccomment period. 

Applicability 

As discussed above, these special 

conditions are applicable to the 747– 

468. Should JAES apply at a later date 

for a supplemental type certificate to 

modify any other model included on 

Type Certificate A20WE, to incorporate 

the same novel or unusual design 

feature, the special conditions would 

apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplanes. It is not a rule of general 

applicability and it affects only the 

applicant who applied to the FAA for 

approval of these features on the 

airplane. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the typecertification basis for Boeing 747–468 

airplanes modified by JAES. 

1. A functional verification must be 

conducted to ensure the adequacy of the 

lift design features that are supposed to 

prevent injury to the lift occupant, lift 

operator, and lift observer. 

2. The occupied lift must be designed 

to withstand the non-emergency load 

conditions imposed by the aircraft 

according to loads report SIE–327–301, 

revision D. 

3. Occupancy or operation of the lift 

must not be permitted during taxi, 

takeoff, landing (TTL), or turbulent 

conditions. 

4. The lift must be stowed for TTL. 

The stowed position requires the lift 

platform positioned at the main-deck 

level with the floor panels closed. 

5. A portable oxygen bottle must be 

present in the lift and easily accessible 

to the occupant. 


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15800 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 

6. Occupancy of the lift must be 

limited to a single occupant secured in 

one of two possible configurations: 

a. The occupant must be secured to a 

medical stretcher that is attached to the 

lift platform. The occupied stretcher 

must be designed to withstand the nonemergency load conditions defined in 

loads report SIE–327–301, revision D. 

b. The occupant must be secured to a 

wheelchair that is attached to the lift 

platform. 

7. Control panels must be located on 

both main and upper decks, connected 

with full duplex audio communications. 

On both operator control units, an 

emergency shut-off switch must be 

installed. In an emergency, this switch 

must immediately interrupt the main 

power supply to the motors. Lift 

operation must be stopped until the 

emergency shut-off switch is reset. As 

soon as one of the operators commands 

operation in a direction, the ‘‘Up’’ and 

‘‘Down’’ option buttons must be disabled 

and the stop button enabled. Before one 

of the operators is able to change the 

lift-travel direction again, the lift must 

first be stopped. 

8. Lift operation must require a 

trained operator at the main-deck 

control panel and a trained observer at 

the upper-deck control panel. 

9. Sensors must be installed to detect 

the following conditions, and to prevent 

the start or continuation of lift travel if 

any conditions are not met: 

a. Upper-deck seat, located on the left 

side of the aircraft and just forward of 

the master-bath bulkhead, is in its most 

forward, outboard position. 

b. Upper-deck master-bedroom/ 

lavatory port bulkhead is opened and 

secured. 

c. Upper-deck shower door is closed 

and secured. 

d. Upper-deck master-lavatory door is 

opened and secured. 

e. Upper-deck floor panels are opened 

and configured to form the protective 

fencing. 

f. Main-deck inboard doors are closed 

and secured. The doors must be 

lockable only from the outside of the 

lift. This ensures that the operator has 

control of this area and that nobody is 

located under the lift. 

g. Aircraft seat-belt-fasten signs must 

not be illuminated. 

10. Sensors must be installed to detect 

the following conditions during 

operation, and to prevent continued lift 

travel if any of these conditions occur: 

a. Over-temperature of lift motors 

and/or power-frequency converter. 

b. Presence of smoke at motors and in 

electrical-control cabinet. 

c. Over-current at the lift motors. 

d. Asynchronous operation of the 

spindles. 

11. A built-in fire extinguisher must 

be installed in the motor and electricalcontrol cabinet. This fire extinguisher 

must be designed to discharge 

automatically upon the occurrence of a 

fire. 

12. The lift must have the provision 

for manual operation in the event of a 

malfunction such as a loss of power to 

the lift and/or associated systems. 

13. A separate battery backup system 

must provide lighting for the lift-control 

system, lift control/sensors, 

communication system, and lift lights 

for a minimum of 10 minutes in the 

event of loss of power to the lift and/or 

associated systems. 

14. Lift placards must be installed 

near or adjacent the control panels 

identified in special condition 7. The 

placards must be stated as follows: 

a. THIS LIFT IS APPROVED FOR 

MOVING ONLY A SINGLE OCCUPANT 

BETWEEN THE MAIN AND UPPER 

DECKS AND ONLY WHEN SECURED 

TO EITHER AN APPROVED MEDICAL 

STRETCHER OR WHEELCHAIR. NO 

OTHER USES OF THIS LIFT ARE 

APPROVED. 

b. DO NOT OPERATE LIFT DURING 

TAXI, TAKEOFF, LANDING, OR 

TURBULENCE. 

c. AN APPROVED MEDICAL 

STRETCHER OR WHEELCHAIR MUST 

BE PROPERLY SECURED TO THE LIFT 

PLATFORM BEFORE OPERATING 

THIS LIFT. 

d. THE LIFT MUST BE STOWED FOR 

TAXI, TAKEOFF, AND LANDING. THE 

STOWED POSITION REQUIRES THE 

LIFT PLATFORM POSITIONED AT 

THE MAIN–DECK LEVEL WITH THE 

FLOOR PANELS CLOSED. 

e. DURING MEDICAL–STRETCHER 

TRANSPORT, ALL PERSONNEL, 

MATERIEL, AND PATIENT 

EXTREMETIES MUST BE POSITIONED 

BETWEEN THE HEAD AND FOOT OF 

THE STRETCHER. 

f. LIFT MAXIMUM CAPACITY: X 

LBS (X KG) 

15. Lift operational-instruction 

placards must be installed near the 

control panels and must describe how 

to: 

a. Configure the lift for operation, 

including ensuring that the bottom of 

the lift is clear of personnel and materiel 

before lowering the lift from the upper 

deck. 

b. Operate the lift. 

c. Stow the lift for non-operation such 

as during TTL and turbulence. 

d. Operate the mechanical-override 

features in the event of a malfunction 

such as a loss of power to the lift and/ 

or associated systems. 

16. Training and related manuals 

must include: 

a. Limitations and procedures for 

normal lift operation. 

b. Backup and override procedure for 

evacuating the lift and returning it to 

TTL configuration. 

17. Special conditions nos. 3, 4, and 

14 must be documented in the 

Limitations section of the airplane flight 

manual. 

Issued in Renton, Washington, on February 

3, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–6618 Filed 3–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1202; Directorate 

Identifier 2010–NM–167–AD; Amendment 

39–16637; AD 2011–06–12] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model MD–90–30 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitive inspections for cracking of the 

left and right upper center skin panels 

of the horizontal stabilizer, and 

corrective action if necessary. This AD 

was prompted by a report of a crack 

found in the upper skin panel at the aft 

inboard corner of a right horizontal 

stabilizer. We are issuing this AD to 

detect and correct cracks in the upper 

center skin panels of the horizontal 

stabilizer. Uncorrected cracks might 

ultimately lead to the loss of overall 

structural integrity of the horizontal 

stabilizer. 

DATES: This AD is effective April 26, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 26, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

phone: 206–544–5000, extension 2; fax: 

206–766–5683; e-mail: 

dse.boecom@boeing.com; Internet: 

https://www.myboeingfleet.com. You 


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