19788 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Rules and Regulations 

Actions Compliance Procedures 

(4) Lubricate the uplock mechanism .................. (i) For Group 1 airplanes: Initially within 300 

hours TIS after October 25, 1972 (the effective date of AD 72–22–01). Repetitively lubricate thereafter at intervals not to exceed 

100 hours TIS.

Follow Beechcraft Service Instructions No. 

0448–211, Rev. I (undated), or Beechcraft 

Service Instructions No. 0448–211 (undated). 

(ii) For Group 2 airplanes: Initially within 300 

hours TIS after May 25, 2007 the effective 

date of this AD. Repetitively lubricate thereafter at intervals not to exceed 100 hours 

TIS. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office, FAA, ATTN: Anthony 

Flores, Aerospace Engineer, 1801 Airport 

Road, Wichita, Kansas 67209; telephone: 

(316) 946–4174; facsimile: (316) 946–4107, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 

(g) AMOCs approved for AD 72–22–01 are 

approved for this AD. 

Material Incorporated by Reference 

(h) You must use Beechcraft Service 

Instructions No. 0448–211, Rev. I (undated), 

or Beechcraft Service Instructions No. 0448–

211 (undated), 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 

Beechcraft Service Instructions No. 0448–211 

(undated), and Beechcraft Service 

Instructions No. 0448–211, Rev. I (undated), 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Raytheon Aircraft Company, 

P.O. Box 85, Wichita, Kansas 67201–0085; 

telephone: (800) 429–5372 or (316) 676–3140. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on April 

6, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–7048 Filed 4–19–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27343; Directorate 

Identifier 2007–SW–05–AD; Amendment 39–

15030; AD 2007–05–51] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters Inc. (MDHI) Model MD600N 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting Airworthiness Directive (AD) 

2007–05–51, which was sent previously 

to all known U.S. owners and operators 

of MDHI Model MD600N helicopters by 

individual letters. This AD requires, 

before further flight, a visual and eddy 

current inspection of each lateral mixer 

output link assembly (mixer link) and 

replacing any cracked mixer link. This 

AD also requires performing an eddy 

current inspection on each mixer link 

before installing it on any helicopter. 

This amendment is prompted by the 

discovery of 3 cracked mixer links. The 

actions specified by this AD are 

intended to detect a crack in the mixer 

link, which could result in failure of the 

mixer link and subsequent loss of 

control of the helicopter. 

DATES: Effective May 7, 2007, to all 

persons except those persons to whom 

it was made immediately effective by 

Emergency AD 2007–05–51, issued on 

February 17, 2007, which contained the 

requirements of this amendment. 

Comments for inclusion in the Rules 

Docket must be received on or before 

June 19, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically; 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically; 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590; 

• Fax: (202) 493–2251; or 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from MD 

Helicopters Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, Arizona 

85215–9734, telephone 1–800–388–

3378, fax 480–346–6813, or on the Web 

at http://www.mdhelicopters.com. 

Examining the Docket 

You may examine the docket that 

contains the AD, any comments, and 

other information on the Internet at 

http://dms.dot.gov, or in person at the 

Docket Management System (DMS) 

Docket Offices between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket Office 

(telephone (800) 647–5227) is located on 

the plaza level of the Department of 

Transportation Nassif Building at the 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

FOR FURTHER INFORMATION CONTACT: Jon 

Mowery, Aviation Safety Engineer, 

FAA, Los Angeles Aircraft Certification 

Office, Airframe Branch, 3960 

Paramount Blvd., Lakewood, California 

90712, telephone (562) 627–5322, fax 

(562) 627–5210. 

SUPPLEMENTARY INFORMATION: On 

February 17, 2007 we issued Emergency 

AD 2007–05–51 for MDHI Model 

MD600N helicopters, which requires, 

before further flight, a visual and eddy 

current inspection of each mixer link 

and replacing any cracked mixer link. 


cprice-sewell on PRODPC61 with RULES
Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Rules and Regulations 19789 

The Emergency AD also requires 

performing an eddy current inspection 

on each mixer link before installing it 

on any helicopter. That action was 

prompted by the discovery of a cracked 

mixer link, part number (P/N) 

600N7636–1, on an in-service MDHI 

Model MD600N helicopter. Cracks were 

also found on two additional mixer 

links, P/N 600N7636–3, which were 

being held as spares. The cracks on all 

three mixer links run through the 

bearing end area of the mixer link and 

emanate from staking marks in the 

mixer link. Cracks in the mixer link, if 

not detected, could result in failure of 

the mixer link and subsequent loss of 

control of the helicopter. 

We have reviewed MDHI Service 

Bulletin No. SB600N–044, dated 

February 16, 2007 (SB), which describes 

procedures for a one-time visual 

inspection and an eddy current 

inspection of the mixer link. The SB 

includes only P/Ns 600N7636–1, and –3 

in its effectivity, however, because the 

exact cause of the cracks is unknown, 

and the –9 and –11 are similar designs, 

we have included them in the 

applicability of this AD. We are also 

requiring an eddy current inspection of 

each affected mixer link before 

installing it on any helicopter. 

Since the unsafe condition described 

is likely to exist or develop on other 

MDHI Model MD600N helicopters of the 

same type design, we issued Emergency 

AD 2007–05–51 to detect a crack in the 

mixer link, which could result in failure 

of the mixer link and subsequent loss of 

control of the helicopter. The AD 

requires, before further flight, the 

following for each mixer link, P/N 

600N7636–1, –3, –9, and –11: 

• Removing each mixer link, and 

visually inspecting, with a bright light 

and a 10x or higher magnifying glass, 

the areas on the ends of the mixer link 

on both sides around the bearing bore 

for any crack, 

• Performing an eddy current 

inspection of each mixer link in the 

bearing end areas, and 

• Replacing any cracked mixer link 

with an airworthy mixer link on which 

an eddy current inspection has been 

performed. 

The AD also requires performing an 

eddy current inspection on each mixer 

link before installing it on any 

helicopter. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the structural integrity 

and controllability of the helicopter. 

Therefore, the actions described 

previously are required before further 

flight, and this AD must be issued 

immediately. 

A one-time flight permit is allowed 

for flying the helicopter to a location 

where the eddy current inspection can 

be performed, provided that no crack is 

found during the visual inspection 

required in paragraph (a) of this AD and 

that the helicopter’s airspeed does not 

exceed 100 knots. 

The requirements of this AD are 

interim actions; the manufacturer 

continues to investigate the cause of the 

cracks and, based on that investigation, 

we will determine either follow-on 

actions or a terminating action for the 

requirements of this AD. 

Since it was found that immediate 

corrective action was required, 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 

letters issued on February 17, 2007 to all 

known U.S. owners and operators of 

MDHI Model MD600N helicopters. 

These conditions still exist, and the AD 

is hereby published in the Federal 

Register as an amendment to 14 CFR 

39.13 to make it effective to all persons. 

We estimate that this AD will affect 

26 helicopters of U.S. registry. It will 

take approximately: 

• 2 work hours to remove, inspect, 

and replace both mixer links on each 

helicopter, 

• 5 work hours for an eddy current 

inspection of both mixer links, 

• $80 per work hour, and 

• $865 for a mixer link, if necessary. 

Based on these figures, we estimate 

the total cost impact of the AD on U.S. 

operators to be $18,885, assuming that 

a visual and eddy current inspection are 

performed on each mixer link installed 

on a helicopter and that 5 of the 52 

mixer links are cracked and need to be 

replaced. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2007–27343; 

Directorate Identifier 2007–SW–05–AD’’

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Regulatory Findings 

We have determined that 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 the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD. See the DMS to examine the 

economic evaluation. 

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. 


cprice-sewell on PRODPC61 with RULES
19790 Federal Register / Vol. 72, No. 76 / Friday, April 20, 2007 / Rules and Regulations 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2007–05–51 MD Helicopters Inc. (MDHI): 

Amendment 39–15030. Docket No. 

FAA–2007–27343; Directorate Identifier 

2007–SW–05–AD. 

Applicability: Model MD600N helicopters, 

with a lateral mixer output link assembly 

(mixer link), part number (P/N) 600N7636–1, 

–3, –9, or –11 installed, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect a crack in the mixer link, which 

could result in failure of the mixer link and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Before further flight: 

(1) Remove each mixer link and visually 

inspect, with a bright light and a 10x or 

higher magnifying glass, the shaded areas 

around the bearing bore for any crack as 

depicted in the following Figure 1: 

(2) Perform an eddy current inspection of 

each mixer link in the bearing end areas. 

(3) Replace any cracked mixer link with an 

airworthy mixer link on which an eddy 

current inspection has been performed. 

Note: MDHI Service Bulletin No. SB600N–

044, dated February 16, 2007, pertains to the 

subject of this AD. 

(b) Perform an eddy current inspection on 

each mixer link before installing it on any 

helicopter. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Los Angeles 

Aircraft Certification Office, FAA, ATTN: Jon 

Mowery, Aviation Safety Engineer, Airframe 

Branch, 3960 Paramount Blvd., Lakewood, 

California 90712, telephone (562) 627–5322, 

fax (562) 627–5210, for information about 

previously approved alternative methods of 

compliance. 

(d) A one-time special flight permit may be 

issued in accordance with 14 CFR 21.197 and 

21.199 to operate the helicopter to a location 

where the eddy current inspection 

requirements of this AD can be accomplished 

provided that no crack is found during the 

visual inspection required in paragraph (a) of 

this AD and that the helicopter’s airspeed 

does not exceed 100 knots. 

(e) This amendment becomes effective on 

May 7, 2007, to all persons except those 

persons to whom it was made immediately 

effective by Emergency AD 2007–05–51, 

issued February 17, 2007, which contained 

the requirements of this amendment. 

Issued in Fort Worth, Texas, on April 5, 

2007. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–7438 Filed 4–19–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27786; Directorate 

Identifier 2007–CE–031–AD; Amendment 

39–15031; AD 2007–09–01] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 182H, 182J, 

182K, 182L, 182M, 182N, 182P, 182Q, 

and 182R Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Model 182 series airplanes that are 

equipped with Air Plains Services 

Corporation Supplemental Type 

Certificate (STC) SA00152WI. This AD 


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