Federal Register / Vol. 79, No. 120 / Monday, June 23, 2014 / Rules and Regulations 35481 

(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 the 

approval must specifically refer to this AD. 

(j) Related Information 

For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles ACO, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5239; fax: 562–627–5210; 

email: chandraduth.ramdoss@faa.gov. 

(k) 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) Boeing Service Bulletin 727–53–0041, 

Revision 6, dated September 5, 1991. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on June 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–13830 Filed 6–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0574; Directorate 

Identifier 2008–SW–22–AD; Amendment 39– 

17766; AD 2014–04–07] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–05– 

03 for Bell Model 407 helicopters. AD 

2003–05–03 required preflight checking 

and repetitively inspecting for a crack in 

certain tailbooms that have been 

redesigned, replacing the tailboom if 

there is a crack, modifying and reidentifying certain tailbooms, installing 

an improved horizontal stabilizer 

assembly, and assigning a 5,000 hour 

time-in-service (TIS) limit. This new AD 

retains the requirements of AD 2003– 

05–03 and requires additional 

inspection requirements. This AD was 

prompted by additional reports of 

cracked tailboom skins. The actions in 

this AD are intended to prevent 

separation of the tailboom and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective July 28, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 28, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 17, 2003 (68 FR 

11967, March 13, 2003). 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron Canada, 12,800 Rue 

de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437–2862 or (800) 363– 

8023, fax (450) 433–0272 or at http://

www.bellcustomer.com/files/. You may 

review 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 in Docket No. 

FAA–2013–0574 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 foreign 

authority’s AD, any incorporated-byreference information, the economic 

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: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5110, fax 

(817) 222–5961, email sharon.y.miles@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–05–03 (68 

FR 11967, March 13, 2003). AD 2003– 

05–03 applied to Bell Model 407 

helicopters. The NPRM published in the 

Federal Register on July 12, 2013 (78 FR 

41877). The NPRM proposed to retain 

the actions of AD 2003–05–03 requiring 

preflight checks and repetitive 

inspections for a crack in certain 

tailbooms that have been redesigned, 

replacing the tailboom if there is a 

crack, modifying and re-identifying 

certain tailbooms, installing an 

improved horizontal stabilizer 

assembly, and assigning a 5,000 hour 

TIS limit. The NPRM also proposed to 

require additional inspection 

requirements. 

The NPRM was prompted by 

Canadian AD No. CF–2008–04, dated 

January 11, 2008 (AD CF–2008–04), 

issued by Transport Canada Civil 

Aviation (TCAA), which is the aviation 

authority for Canada, to correct an 

unsafe condition for Bell Model 407 

helicopters. TCAA advises that there 

have been several reports of cracks to 

the tailboom skin on the left side in the 

area of the horizontal stabilizer. AD CF– 

2008–04 mandates new inspection 

requirements based on the 

manufacturer’s service information 

discussed in the ‘‘Related Service 

Information’’ section under 

SUPPLEMENTARY INFORMATION in the 

preamble of this final rule. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 


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we did not receive any comments on the 

NPRM (78 FR 41877, July 12, 2013). 

FAA’s Determination 

The helicopter has been approved by 

the aviation authority of Canada and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCAA, its 

technical representative, has notified us 

of the unsafe condition described in the 

TCAA AD. We are issuing this AD 

because we evaluated all information 

provided by TCAA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type design and that air safety 

and the public interest require adopting 

the AD requirements as proposed except 

we are removing one of the figures in 

this AD to meet current publication 

requirements. This change is consistent 

with the intent of the proposals in the 

NPRM (78 FR 41877, July 12, 2013), and 

will not increase the economic burden 

on any operator nor increase the scope 

of this AD. 

Differences Between This AD and the 

TCAA AD 

This AD does not require you to 

contact the manufacturer. This AD does 

not state that replacing the affected 

tailboom with tailboom, part number (P/ 

N) 407–030–801–201, –203, –205, or 

later numbers constitutes terminating 

action because installing other partnumbered tailbooms than those listed in 

the applicability of this AD may also 

result in terminating action for the 

requirements of this AD. 

Related Service Information 

We reviewed Bell Technical Bulletin 

(TB) No. 407–01–33, dated August 29, 

2001; Bell Alert Service Bulletin (ASB) 

No. 407–99–26, Revision B, dated June 

14, 2001, and Revision C, dated 

February 28, 2002; Bell ASB No. 407– 

07–80, dated August 27, 2007; and Bell 

ASB No. 407–01–48, Revision C, dated 

August 27, 2007. 

Bell issued TB No. 407–01–33 for 

certain serial-numbered Bell Model 407 

helicopters to improve the installation 

of the horizontal stabilizer by specifying 

an inspection for and correction of any 

gaps between the horizontal stabilizer 

attachment supports and the stabilizer 

surface. Bell issued ASB No. 407–99–26, 

Revision B, to specify an inspection and 

a preflight check of the left-hand side of 

the tailboom skin and fasteners at the 

horizontal stabilizer attachment area for 

Bell Model 407 helicopters with certain 

part-numbered tailbooms. Bell later 

revised ASB No. 407–99–26 to Revision 

C to remove one part-numbered 

tailboom from the applicability of the 

ASB. 

In ASB No. 407–07–80, Bell states it 

has received additional reports of 

cracked tailboom skins, P/N 407–030– 

801–157, affecting tailboom assemblies, 

P/N 407–530–014–101 and –103 

(modified per AD 2003–05–03 (68 FR 

11967, March 13, 2003), reference ASB 

No. 407–01–48, Revision B, dated April 

25, 2002), and original production 

tailboom assembly, P/N 407–030–801– 

107. Each report indicated a crack above 

the left side upper stabilizer attachment 

support at Station 98.89. Further 

investigation conducted by Bell 

revealed other areas of the tailbooms 

require additional attention. Thus, ASB 

No. 407–07–080 contains procedures for 

preparing the tailboom for repetitive 

inspection, preflight checking the 

tailboom, and repetitively inspecting the 

tailboom. Bell specifies that replacing 

the affected tailboom assembly, P/N 

407–530–014–101, –103 or 407–030– 

801–107, with tailboom assembly, P/N 

407–030–801–201, –203, –205, or later 

dash numbers is terminating action for 

Bell ASB No. 407–07–80. 

In ASB No. 407–01–48, Bell states 

that since issuing Revision C of ASB No. 

407–99–26, it received additional 

reports of cracks in the upper skins, 

which originated from holes where the 

fasteners are installed at the forward 

and aft section of the left upper 

stabilizer support, P/N 407–023–800– 

117. ASB No. 407–01–48 contains 

procedures for inspecting the tailboom 

on the left side where the fasteners are 

installed, installing an improved 

horizontal stabilizer assembly, reidentifying the tailboom, and assigning 

a 5,000-hour TIS life limit to the 

tailboom. 

Costs of Compliance 

We estimate that this AD will affect 

about 464 helicopters of U.S. registry. 

We estimate that operators will incur 

the following costs in order to comply 

with this AD. We estimate the time for 

conducting pilot checks is minimal and 

thus we are assuming there is no cost. 

It will take about .5 work-hour to 

perform the annotations in the 

helicopter records, 1.5 work hours to 

prepare the inspection area and do the 

magnification inspection, and 2.5 work 

hours to do the repetitive 100-hour TIS 

inspections at an average labor rate of 

$85 per work-hour. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators will be $1,445 per 

helicopter and $670,480 for the U.S. 

operator fleet to do the checks and 

inspections, based on 6 repetitive 

inspections the first year. The previous 

AD affected 284 helicopters, and we 

estimated 3.5 work hours to do the 

initial inspection, 1.5 work hours to do 

the recurring inspections, and 18 work 

hours to do the modification at an 

average labor rate of $60 per work hour. 

Required parts were estimated at $1,244 

per helicopter. Based on these figures, 

the total cost of the AD on U.S. 

operators was estimated to be $3,254 per 

helicopter or $924,136, based on 8 

repetitive inspections per year. 

According to Bell, the cost of a new 

tailboom is $82,850. Per Bell ASB No. 

407–07–80, the costs to replace the 

tailboom may be covered under 

warranty, thereby reducing the cost 

impact on affected individuals. We do 

not control warranty coverage by Bell. 

We have included all costs in our cost 

estimate. 

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 

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 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 to the extent that it justifies 

making a regulatory distinction; and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 


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Federal Register / Vol. 79, No. 120 / Monday, June 23, 2014 / Rules and Regulations 35483 

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 

removing Airworthiness Directive (AD) 

2003–05–03 (68 FR 11967, March 13, 

2003) and by adding the following new 

AD: 

2014–04–07 Bell Helicopter Textron 

Canada: Amendment 39–17766; Docket 

No. FAA–2013–0574; Directorate 

Identifier 2008–SW–22–AD. 

(a) Applicability 

This AD applies to Model 407 helicopters, 

serial numbers 53000 through 53475, with 

tailboom, part number (P/N) 407–030–801– 

101, –105, or –107, or 407–530–014–101 or 

–103, installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

cracks in the tailboom skin on the left side 

in the area of horizontal stabilizer, which 

could result in separation of the tailboom and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2003–05–03, 

Amendment 39–13079 (68 FR 11967, March 

13, 2003). 

(d) Effective Date 

This AD becomes effective July 28, 2014. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) For tailboom, P/Ns 407–030–801–101 

and –105: 

(i) Unmodified per Bell Alert Service 

Bulletin (ASB) 407–01–48, Revision C, dated 

August 27, 2007 (ASB 407–01–48): 

(A) Before the first flight of each day, 

visually check the tailboom for a crack, as 

depicted in Figure 1 to Paragraph (f)(1)(i)(A) 

of this AD. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(B) For a tailboom with 600 or more hours 

time-in-service (TIS), within 25 hours TIS 

and thereafter at intervals not to exceed 50 

hours TIS, visually inspect the tailboom for 

a crack using a 10X or higher magnifying 

glass by following the Accomplishment 

Instructions, Part II, of Bell ASB 407–99–26, 

Revision C, dated February 28, 2002, except 

this AD does not require you to contact Bell. 

(ii) Within 600 hours TIS, but not later 

than 30 days: 

(A) Modify and re-identify each tailboom, 

P/N 407–030–801–101 as 407–530–014–101, 

and P/N 407–030–801–105 as 407–530–014– 

103, by following the Accomplishment 

Instructions, Parts I and III, of ASB 407–01– 

48. 

(B) Install improved horizontal stabilizer 

assembly, P/N 407–023–800–ALL, by 

following Bell Technical Bulletin No. 407– 

01–33, dated August 29, 2001, except this AD 

does not require you to contact Bell. 

(2) For tailboom, P/Ns 407–530–014–101 

and –103, and P/N 407–030–801–107: 

(i) Before further flight after the tailboom 

is modified and re-identified, revise the 

Airworthiness Limitations section of the 

maintenance manual by establishing a 

retirement life of 5,000 hours TIS. Create a 


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Federal Register / Vol. 79, No. 120 / Monday, June 23, 2014 / Rules and Regulations 35485 

component history card or equivalent record 

and assign a life limit of 5,000 hours TIS by 

following the Accomplishment Instructions, 

Part IV, of ASB 407–01–48. 

(ii) Within 25 hours TIS or 30 days, 

whichever occurs first, prepare the tailboom 

for daily visual checks and recurring 

inspections and inspect the tailboom for a 

crack by following the Accomplishment 

Instructions, Part II, Steps 1.a) through 1.f), 

of Bell ASB 407–07–80, dated August 27, 

2007 (ASB 407–07–80). 

(iii) Thereafter, before the first flight of 

each day, clean the area on the tailboom 

where paint has been removed at the upper 

and lower attachment support areas of the 

horizontal stabilizer and visually check that 

area of the tailboom for a crack. 

(iv) Within 100 hours TIS and thereafter at 

intervals not to exceed 100 hours TIS, using 

a 10X or higher power magnifying glass, 

inspect each tailboom for a loose rivet, a 

crack, skin corrosion, or any other damage, 

by following the Accomplishment 

Instructions, Part IV, Steps 1 through 6, of 

ASB 407–07–80, except this AD does not 

require you to contact Bell. If there is 

corrosion within an allowable tolerance, 

repair each area of corrosion. 

(3) If there is a crack, before further flight, 

replace the tailboom. 

(4) If there is no crack, make sure both of 

the inspection area surfaces are dry and 

protect each reworked area with a thin coat 

of clear coating. 

(5) The actions required by paragraphs 

(f)(1)(i)(A) and (f)(2)(iii) of this AD may be 

performed by the owner/operator (pilot) 

holding at least a private pilot certificate and 

must be entered into the aircraft records 

showing compliance with this AD in 

accordance with 14 CFR 43.9 (a)(1) through 

(4) and 91.417(a)(2)(v). This record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

(1) Bell Alert Service Bulletin No. 407–99– 

26, Revision B, dated June 14, 2001, which 

is not incorporated by reference, contains 

additional information about the subject of 

this AD. For this service information, contact 

Bell Helicopter Textron Canada, 12,800 Rue 

de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437 2862 or (800) 363–8023, 

fax (450) 433–0272 or at http://www.bell

customer.com/files/. You may review service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2008–04, dated January 11, 2008. 

You may view the TCCA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0574. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code is 5300: Rotorcraft Tail Boom, and 

5302: Middle Section. 

(j) 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. 

(3) The following service information was 

approved for IBR on July 28, 2014. 

(i) Bell Helicopter Textron Alert Service 

Bulletin (ASB) No. 407–01–48, Revision C, 

dated August 27, 2007. 

(ii) Bell Helicopter Textron ASB No. 407– 

07–80, dated August 27, 2007. 

(4) The following service information was 

approved for IBR on April 17, 2003 (68 FR 

11967, March 13, 2003). 

(i) Bell Helicopter Textron ASB No. 407– 

99–26, Revision C, dated February 28, 2002. 

(ii) Bell Helicopter Textron Technical 

Bulletin No. 407–01–33, dated August 29, 

2001. 

(5) For Bell service information identified 

in this AD, contact Bell Helicopter Textron 

Canada, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272 or at 

http://www.bellcustomer.com/files/. 

(6) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(7) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on May 21, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–13263 Filed 6–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1056; Directorate 

Identifier 2013–CE–046–AD; Amendment 

39–17849; AD 2014–10–02] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Luftfahrt GmbH Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2006–11– 

19 for Dornier Luftfahrt GmbH Model 

Dornier 228–100, 228–101, 228–200, 

228–201, 228–202, and 228–212 

airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as chafed 

or damaged wiring on the flight deck 

overhead panels (5VE and 6VE). We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective July 28, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 28, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

1056; or in person at the Docket 

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 service information identified in 

this AD, contact RUAG Aerospace 

Services GmbH, Dornier 228 Customer 

Support, P.O. Box 1253, 82231 

Wessling, Germany; telephone: +49 (0) 

8153–30 2220; fax: +49 (0) 8153–30 

4258; email: custsupport.dornier228@

ruag.com; Internet: http://

www.ruag.com/en/Aviation/Aviation_

Home. You may view this referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. 


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