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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Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 15801 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Roger Durbin, Aerospace Engineer, Los 

Angeles ACO, Airframe Branch, ANM– 

120L, FAA, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5233; fax: 562–627–5210; 

e-mail: Roger.Durbin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

December 23, 2010 (75 FR 80742). That 

NPRM proposed to require repetitive 

inspections for cracking of the left and 

right upper center skin panels of the 

horizontal stabilizer, and corrective 

action if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Conclusion 

We reviewed the relevant data, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 19 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ........... 4 work-hours × $85 per hour = 

$340 per inspection cycle.

$0 $340 per inspection cycle .............. $6,460 per inspection cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Skin panel replacement ................................................ 648 work-hours × $85 per hour = $55,080 .................. $55,608 $110,688 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


Emcdonald on DSK2BSOYB1PROD with RULES
15802 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2011–06–12 The Boeing Company: 

Amendment 39–16637; Docket No. 

FAA–2010–1202; Directorate Identifier 

2010–NM–167–AD. 

Effective Date 

(a) This AD is effective April 26, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model MD–90–30 airplanes, 

certificated in any category. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

Unsafe Condition 

(e) This AD was prompted by a report of 

a crack found in the upper center 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 

panel of the horizontal stabilizer. 

Uncorrected cracks might ultimately lead to 

the loss of overall structural integrity of the 

horizontal stabilizer. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections 

(g) Before the accumulation of 20,000 total 

flight cycles, or within 3,778 flight cycles 

after the effective date of this AD, whichever 

occurs later, do eddy current inspections to 

detect cracking of the left and right upper 

center skin panels of the horizontal stabilizer, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A015, dated July 16, 2010. 

(1) If no crack is found during any 

inspection required by paragraph (g) of this 

AD, repeat the applicable inspections 

thereafter at the applicable times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin MD90–55A015, dated July 

16, 2010. 

(2) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, replace the skin 

panel with a serviceable skin panel, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A015, dated July 16, 2010. Within 

20,000 flight cycles after the replacement, do 

eddy current inspections as required by 

paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Related Information 

(i) For more information about this AD, 

contact Roger Durbin, Aerospace Engineer, 

Los Angeles ACO, Airframe Branch, ANM– 

120L, FAA, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5233; fax: 562–627–5210; e-mail: 

Roger.Durbin@faa.gov. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin MD90–55A015, dated July 16, 2010, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin MD90–55A015, 

dated July 16, 2010, under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) 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. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 9, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–6249 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–2011–0212; Directorate 

Identifier 2010–SW–055–AD; Amendment 

39–16632; AD 2011–06–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Model EC130 B4 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Eurocopter Model EC130 B4 helicopters. 

This action requires identifying and 

inspecting a certain emergency flotation 

gear unit ‘‘1G’’ (1G unit). This action also 

requires modification of certain affected 

1G units. This amendment is prompted 

by an uncommanded in-flight 

deployment of the emergency flotation 

gear when it was not armed by the crew. 

The actions specified in this AD are 

intended to prevent an uncommanded 

in-flight deployment of the emergency 

flotation gear, unexpected deceleration 

and pitch down movement of the 

helicopter, and subsequent loss of 

control of the helicopter. 

DATES: Effective April 6, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of April 6, 

2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

May 23, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 


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