Federal Register / Vol. 77, No. 145 / Friday, July 27, 2012 / Rules and Regulations 44113 

Rotorcraft Flight Manual Supplement 

(RFMS): 

(i) OEI performance information and 

emergency procedures, providing the 

maximum weight that will provide a 

minimum clearance of 15 feet above the 

surface, following failure of the critical 

engine in a hover. The maximum weight 

must be presented as a function of the 

hover height for the temperature and 

pressure altitude range requested for 

certification. The effects of wind must 

be reflected in the hover performance 

information. 

(ii) Hover OGE performance with the 

critical engine inoperative for OEI 

continuous and time-limited power 

ratings for those weights, altitudes, and 

temperatures for which certification is 

requested. 

Note: These OEI performance requirements 

do not replace performance requirements that 

may be needed to comply with the 

airworthiness or operational standards (14 

CFR 29.865 or 14 CFR part 133) for external 

loads or human external cargo. 

(f) RFMS. 

(1) The RFMS must contain, at a 

minimum: 

(i) Limitations necessary for safe 

operation of the SAR system to include: 

(A) Minimum crew requirements. 

(B) Maximum SAR weight. 

(C) Engagement criteria for each of the 

SAR modes to include MUH (as 

determined in paragraph (c)(3)). 

(ii) Normal and emergency procedures 

for operation of the SAR system (to 

include operation of the hoist operator 

control), with AFCS failure modes, 

AFCS degraded modes, and engine 

failures. 

(iii) Performance information: 

(A) OEI performance and height-loss. 

(B) Hover OGE performance 

information, utilizing OEI continuous 

and time-limited power ratings. 

(C) The maximum wind envelope 

demonstrated in flight test. 

(g) Flight Demonstration. 

(1) Before approval of the SAR 

system, an acceptable flight 

demonstration of all the coupled SAR 

modes is required. 

(2) The AFCS must provide fail-safe 

operations during coupled maneuvers. 

The demonstration of fail-safe 

operations must include a pilot 

workload assessment associated with 

manually flying the aircraft to an 

altitude greater than 200 feet above the 

surface and an airspeed of at least the 

best rate of climb airspeed (Vy). 

(3) For any failure condition of the 

SAR system not shown to be extremely 

improbable, the pilot must be able to 

make a smooth transition from one 

flight mode to another without 

exceptional piloting skill, alertness, or 

strength. 

(4) Failure conditions that are not 

shown to be extremely improbable must 

be demonstrated by analysis, ground 

testing, or flight testing. For failures 

demonstrated in flight, the following 

normal pilot recovery times are 

acceptable: 

(i) Transition modes (Cruise-to-Hover/ 

Hover-to-Cruise) and Hover modes: 

Normal pilot recognition plus 1 second. 

(ii) Cruise modes: Normal pilot 

recognition plus 3 seconds. 

(5) All AFCS malfunctions must 

include evaluation at the low-speed and 

high-power flight conditions typical of 

SAR operations. Additionally, AFCS 

hard-over, slow-over, and oscillatory 

malfunctions, particularly in yaw, 

require evaluation. AFCS malfunction 

testing must include a single or a 

combination of failures (e.g., erroneous 

data from and loss of the radio altimeter, 

attitude, heading, and altitude sensors) 

that are not shown to be extremely 

improbable. 

(6) The flight demonstration must 

include the following environmental 

conditions: 

(i) Swell into wind. 

(ii) Swell and wind from different 

directions. 

(iii) Cross swell. 

(iv) Swell of different lengths (short 

and long swell). 

Issued in Fort Worth, Texas, on July 18, 

2012. 

Kimberly K. Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–18199 Filed 7–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0675; Directorate 

Identifier 2012–NM–120–AD; Amendment 

39–17131; AD 2012–13–51] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP (Type Certificate 

Previously Held by Israel Aircraft 

Industries, Ltd.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Gulfstream Aerospace LP (Type 

Certificate previously held by Israel 

Aircraft Industries, Ltd.) Model 

Gulfstream G150 airplanes. This 

emergency AD was sent previously to 

all known U.S. owners and operators of 

these airplanes. This AD requires a onetime detailed or borescope inspection of 

the left- and right-hand inboard vent 

holes for debris or obstructions, and 

repair if necessary. This AD was 

prompted by a report indicating that an 

inboard vent tube hole was completely 

covered with sealant, which blocked 

airflow through the vent. Under these 

conditions, the rise of internal pressure 

during pressure fueling or due to 

thermal expansion is sufficient to 

damage the wing. We are issuing this 

AD to detect and correct compromised 

integrity of the wing structure. 

DATES: This AD is effective August 13, 

2012 to all persons except those persons 

to whom it was made immediately 

effective by emergency AD 2012–13–51, 

issued on June 26, 2012, which 

contained the requirements of this 

amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication identified in the 

AD as of August 13, 2012. 

We must receive comments on this 

AD by September 10, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, P.O. Box 2206, Mail 

Station D–25, Savannah, Georgia 31402– 

2206; telephone 800–810–4853; fax 

912–965–3520; email 

pubs@gulfstream.com; Internet http:// 

www.gulfstream.com/product_support/ 

technical_pubs/pubs/index.htm. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations Office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 


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44114 Federal Register / Vol. 77, No. 145 / Friday, July 27, 2012 / Rules and Regulations 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Groves, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

227–1503; fax: 425–227–1149; email: 

tom.groves@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 26, 2012, we issued 

emergency AD 2012–13–51, which 

requires a one-time detailed or 

borescope inspection of the left- and 

right-hand inboard vent holes for debris 

or obstructions, and repair if necessary. 

Emergency AD 2012–13–51 also 

requires reporting positive inspection 

findings to the manufacturer. This 

action was prompted by a report from 

the Civil Aviation Authority of Israel 

(CAAI), which is the airworthiness 

authority for Israel, indicating that an 

unsafe condition may exist on 

Gulfstream Aerospace LP Model 

Gulfstream G150 airplanes. The CAAI 

advises that fasteners protruding from 

the lower wing surface were discovered 

during a post-flight inspection. 

Investigation revealed structural damage 

to (and separation of) ribs from wing 

planks. 

Further inspection showed that the 

inboard vent tube hole was completely 

covered with sealant, which blocked 

airflow through the vent. This condition 

was also found on some airplanes in 

production. Under these conditions, the 

rise of internal pressure during pressure 

fueling or due to thermal expansion is 

sufficient to damage the wing. This 

condition, if not detected and corrected, 

could compromise the integrity of the 

wing structure. 

Relevant Service Information 

Gulfstream Aerospace LP has issued 

Gulfstream G150 Alert Service Bulletin 

150–28A–146, dated June 22, 2012. The 

service information describes 

procedures for a one-time detailed or 

borescope inspection of the left- and 

right-hand inboard vent holes for debris 

and obstructions. The service 

information specifies to contact the 

manufacturer if any debris or 

obstruction is found. The CAAI 

mandated this service bulletin and 

issued Emergency Airworthiness 

Directive 28–12–06–18, dated June 24, 

2012 (referred to after this as ‘‘the 

MCAI’’), to ensure the continued 

airworthiness of these airplanes in 

Israel. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Since the unsafe condition described 

is likely to exist or develop on other 

airplanes of the same type design, we 

issued emergency AD 2012–13–51 to 

detect and correct compromised 

integrity of the wing structure. The AD 

requires a one-time detailed or 

borescope inspection of the left- and 

right-hand inboard vent holes for debris 

or obstructions, and repair if necessary. 

The AD also requires reporting positive 

inspection findings to the manufacturer. 

We found that immediate corrective 

action was required; therefore, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

notices issued on June 26, 2012, to all 

known U.S. owners and operators of 

Gulfstream Aerospace LP (Type 

Certificate previously held by Israel 

Aircraft Industries, Ltd.) Model 

Gulfstream G150 airplanes. These 

conditions still exist, and the AD is 

hereby published in the Federal 

Register as an amendment to section 

39.13 of the Federal Aviation 

Regulations (14 CFR 39.13) to make it 

effective to all persons. 

Interim Action 

We consider this AD interim action. 

We may consider further rulemaking 

when additional information is 

available. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because we received a report 

indicating that an inboard vent tube 

hole was completely covered with 

sealant, which blocked airflow through 

the vent. Under these conditions, the 

rise of internal pressure during pressure 

fueling or due to thermal expansion is 

sufficient to damage the wing. We are 

issuing this AD to detect and correct 

compromised integrity of the wing 

structure. Therefore, we find that notice 

and opportunity for prior public 

comment are impracticable and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2012–0675 and Directorate 

Identifier 2012–NM–120–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 58 

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 ............................. Up to 18 work-hours × $85 per hour = up to $1,530 ......... $0 Up to $1,530 ..... Up to $88,740. 


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Federal Register / Vol. 77, No. 145 / Friday, July 27, 2012 / Rules and Regulations 44115 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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: 

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): 

2012–13–51 Gulfstream Aerospace LP 

(Type Certificate Previously Held by 

Israel Aircraft Industries, Ltd.): 

Amendment 39–17131; Docket No. 

FAA–2012–0675; Directorate Identifier 

2012–NM–120–AD. 

(a) Effective Date 

This AD is effective August 13, 2012 to all 

persons except those persons to whom it was 

made immediately effective by emergency 

AD 2012–13–51, issued on June 26, 2012, 

which contained the requirements of this 

amendment. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Gulfstream Aerospace 

LP (Type Certificate previously held by Israel 

Aircraft Industries, Ltd.) Model Gulfstream 

G150 airplanes, certificated in any category, 

serial numbers 201 through 290 inclusive. 

(d) Subject 

Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that an inboard vent tube hole was 

completely covered with sealant, which 

blocked airflow through the vent. Under 

these conditions, the rise of internal pressure 

during pressure fueling or due to thermal 

expansion is sufficient to damage the wing. 

We are issuing this AD to detect and correct 

compromised integrity of the wing structure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Repair 

Before further flight: Do a one-time 

detailed or borescope inspection of the leftand right-hand inboard vent holes for debris 

and obstructions, in accordance with the 

Accomplishment Instructions of Gulfstream 

G150 Alert Service Bulletin 150–28A–146, 

dated June 22, 2012. If any debris or 

obstruction is found, before further flight, 

repair in accordance with a method approved 

by either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the Civil Aviation Authority of Israel 

(CAAI) (or its delegated agent). 

(h) Reporting Requirement 

(1) Submit a report of positive findings of 

the inspection required by paragraph (g) of 

this AD to Gulfstream Aerospace CMP, fax 

800–944–1775 or 912–963–0265, at the 

applicable time specified in paragraph 

(h)(1)(i) or (h)(1)(ii) of this AD. The report 

must include the inspection date and results, 

a description of any finding, the airplane 

serial number, and the number of flight hours 

and landings on the airplane. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

(2) A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

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 

International Branch, send it to the attention 

of the person identified in the Related 

Information section of this AD. Information 

may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 

(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. The AMOC 

approval letter must specifically reference 

this AD. 

(j) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are allowed provided the criteria 

in this paragraph are met. A general visual 

inspection must be done to detect fuel leaks, 

skin distortion, protruding fasteners, and 

loose fasteners of the left- and right-hand 

lower wing skins. A special flight permit is 

not allowed if there is any finding from the 

inspection. If there are no findings from the 

inspection, a special flight permit is allowed, 

provided the total wing tank fuel quantity of 


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44116 Federal Register / Vol. 77, No. 145 / Friday, July 27, 2012 / Rules and Regulations 

the airplane (i.e., total of both wing tanks) is 

limited to 3,500 pounds or less. 

(k) Related Information 

(1) For further information about this AD, 

contact Tom Groves, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–227–1503; fax: 425 227– 

1149; email: tom.groves@faa.gov. 

(2) Refer to MCAI Israeli Emergency 

Airworthiness Directive 28–12–06–18, dated 

June 24, 2012; and Gulfstream G150 Alert 

Service Bulletin 150–28A–146, dated June 

22, 2012; for related information. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Gulfstream G150 Alert Service Bulletin 

150–28A–146, dated June 22, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, P.O. Box 2206, Mail Station 

D–25, Savannah, Georgia 31402–2206; 

telephone 800–810–4853; fax 912–965–3520; 

email pubs@gulfstream.com; Internet http:// 

www.gulfstream.com/product_support/ 

technical_pubs/pubs/index.htm. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) 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 July 13, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–17955 Filed 7–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0356; Directorate 

Identifier 2011–SW–067–AD; Amendment 

39–17128; AD 2012–14–14] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Eurocopter Deutschland GmbH (ECD) 

MBB–BK 117 A–3, MBB–BK 117 A–4, 

MBB–BK B–1, MBB–BK 117 B–2, and 

MBB–BK C–1 helicopters equipped with 

a certain external-hoist system (hoist 

system). This AD requires deactivating 

the entire hoist system or deactivating 

the hoist system cable cutter function on 

the hoist system operator control handle 

(operator handle). This AD was 

prompted by an uncommanded 

activation of the hoist cable cutter 

function on an MBB–BK117 C–1 

helicopter. The actions of this AD are 

intended to prevent uncommanded 

cutting of the hoist cable and 

subsequent injury to persons being 

lifted by the hoist. 

DATES: This AD is effective August 31, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of August 31, 2012. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

telephone (972) 641–0000 or (800) 232– 

0323, fax (972) 641–3775, or at http:// 

www.eurocopter.com/techpub. 

You may review the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas 76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 

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

Friday, except Federal holidays. The AD 

docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 4, 2012, at 77 FR 20321, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to ECD 

Model MBB–BK 117 A–3, MBB–BK 117 

A–4, MBB–BK B–1, MBB–BK 117 B–2, 

and MBB–BK C–1 helicopters equipped 

with a certain hoist system. That NPRM 

proposed to require deactivating the 

entire hoist system or deactivating the 

hoist system cable cutter function on the 

operator handle. The proposed 

requirements were intended to prevent 

uncommanded cutting of the hoist cable 

and subsequent injury to persons being 

lifted by the hoist. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2011– 

0126, dated July 1, 2011 (EASA AD 

2011–0126), to correct an unsafe 

condition for the ECD Model MBB–BK 

117 A–3, MBB–BK 117 A–4, MBB–BK 

B–1, MBB–BK 117 B–2, and MBB–BK 

C–1 helicopters equipped with a certain 

hoist system. EASA AD 2011–0126 

requires deactivation of the affected 

external hoist system by pulling and 

securing the related circuit breakers, or 

by removing the hoist boom. 

After EASA AD 2011–0126 was 

issued, it was discovered that pulling 

the circuit breaker WARN ANN II 

degraded the annunciator system’s 

redundant power supply, so that pilots 

could not be warned of a second 

helicopter system failure. Prompted by 

these findings, EASA issued 

superseding EASA AD No. 2011–0131, 

dated July 8, 2011 (EASA AD 2011– 

0131), to require pulling only three 

circuit breakers (CABLE CUTTER, 

WINCH CONT, and WINCH BOOM), 

while circuit breaker WARN ANN II 

remains inserted. 

EASA advises that since EASA AD 

2011–0131 was issued ‘‘a corrective 

action has been developed to establish 

an adequate safety level, while a 

terminating action is under 


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