3050 Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26134; Directorate 

Identifier 2006–CE–56–AD; Amendment 39–

14898; AD 2007–02–11] 

RIN 2120–AA64 

Airworthiness Directives; EXTRA 

Flugzeugproduktions-und VertriebsGmbH Models EA–300, EA–300S, EA–

300L, and EA–300/200 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) to 

supersede AD 2002–21–11, which 

applies to certain EXTRA Flugzeugbau 

GmbH (EXTRA) Model EA–300S 

airplanes. AD 2002–21–11 currently 

requires you to inspect, using a 

fluorescent dye check penetrant 

method, the upper longeron at the 

horizontal stabilizer attachment for 

cracks, repair any cracks found, and 

modify the horizontal stabilizer. That 

AD also requires a limit on operation to 

the Normal category until the initial 

inspection and modification on 

airplanes with less than 200 hours timein-service is done. Since we issued AD 

2002–21–11, cracks have been found on 

Models EA–300L and EA–300/200 

airplanes. Consequently, this AD adds 

airplanes to the Applicability section 

and requires you to inspect and modify 

the upper longeron at the horizontal 

stabilizer attachment. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the airworthiness authority for 

Germany. We are issuing this AD to 

detect, correct, and prevent cracks in the 

upper longeron at the horizontal 

stabilizer attachment, which could 

result in structural failure of the aft 

fuselage. This failure could lead to loss 

of control. 

DATES: This AD becomes effective on 

February 28, 2007. 

As of February 28, 2007, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: For service information 

identified in this AD, contact EXTRA 

Flugzeugproduktions-und VertriebsGmbH, Schwarze Heide 21, D–46569 

Huenxe, Germany; fax: (+49)-2858–

9137–42. 

To view the AD docket, go to the 

Docket Management Facility, U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2006–26134; Directorate Identifier 

2006–CE–56–AD. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 15, 2006, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain EXTRA Flugzeugproduktionsund Vertriebs-GmbH (EXTRA) Models 

EA–300, EA–300S, EA–300L, and EA–

300/200 airplanes. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on November 22, 2006 (71 FR 67499). 

The NPRM proposed to supersede AD 

2002–21–11, Amendment 39–12917 (67 

FR 65479, October 25, 2002), with a new 

AD that would require you to do the 

following: 

• Inspect the upper longeron at the 

horizontal stabilizer attachment for 

cracks; 

• Reinforce the upper longeron in the 

area of the horizontal stabilizer 

attachment; and 

• Install V-tubes to reinforce fuselage 

frame underneath the horizontal 

stabilizer attachment bracket on Models 

EA–300S and EA–300L airplanes only. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the proposal or on the determination of 

the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

• 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. 

Differences Between the European 

Authority AD, the Service Bulletin, and 

This AD 

EASA AD No. 2006–0281, dated 

September 14, 2006, and EXTRA 

Service Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006, allow 50-hour 

repetitive inspections of the horizontal 

stabilizer attachment with the option of 

installing the modification kits as a 

terminating action for the repetitive 

inspections for certain affected 

airplanes. This AD does not allow 

continued repetitive inspections. 

The FAA has determined that longterm continued operational safety is 

better assured by design changes that 

remove the source of the problem rather 

than by repetitive inspections or other 

special procedures. 

Costs of Compliance 

We estimate that this AD affects 134 

airplanes in the U.S. registry. 

We estimate the following costs to do 

the inspection: 

Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 

24 work-hours × $80 per hour = $1,920 ............................. Not applicable ......... $1,920 ................................ $1,920 × 134 = $257,280. 

We estimate the following costs to do 

the modifications: 

Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 

40 work-hours × $80 per hour = $3,200 ............................. $200 ........................ $3,200 + $200 = $3,400 .... $3,400 × 134 = $455,600. 


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Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 3051 

For airplanes still covered under 

warranty, the manufacturer will provide 

warranty credit for up to 35 work-hours 

for the inspection and modification 

work, as stated on page 8 of EXTRA 

Service Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

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 AD. 

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 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 a summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2006–26134; 

Directorate Identifier 2006–CE–56–AD’’

in your request. 

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 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. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2002–21–11, Amendment 39–12917 (67 

FR 65479, October 25, 2002) and adding 

the following new AD: 

2007–02–11 EXTRA Flugzeugproduktionsund Vertriebs-GmbH: Amendment 39–

14898; Docket No. FAA–2006–26134; 

Directorate Identifier 2006–CE–56–AD. 

Effective Date 

(a) This AD becomes effective on February 

28, 2007. 

Affected ADs 

(b) This AD supersedes AD 2002–21–11, 

Amendment 39–12917. 

Applicability 

(c) This AD applies to the following 

airplanes that are certificated in any category: 

Models Serial Nos. 

EA–300 ........................ 01 through 62. 

EA–300L ...................... 01 through 71, 73 through 77, 79 through 83, 85 through 89, 91, and 92. 

EA–300S ..................... 01 through 29. 

EA–300/200 ................. 01 through 31 and 1032 through 1039. 

Unsafe Condition 

(d) This AD is the result from mandatory 

continuing airworthiness information (MCAI) 

issued by the airworthiness authority for 

Germany. The actions specified in this AD 

are intended to detect, correct, and prevent 

cracks in the upper longeron at the horizontal 

stabilizer attachment, which could result in 

structural failure of the aft fuselage. This 

failure could lead to loss of control. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Inspect, using a fluorescent dye 

penetrant method, the upper longeron at the horizontal stabilizer 

attachment for cracks, as applicable. You may take ‘‘unless already done’’ credit for the inspections if you previously used Extra 

Service Bulletin No. 300–2–95 

(pages 2–6 at Issue: C, dated 

July 15, 1998; and pages 1 and 

7 through 11 at Issue: D, dated 

January 30, 2001).

(i) For Models EA–300S airplanes: Upon accumulating 250 hours 

time-in-service (TIS) after December 17, 2002 (the effective date of 

AD 2002–21–11) or within the next 50 hours TIS after February 28, 

2007 (the effective date of this AD), whichever occurs first. (ii) For 

Models EA–300, EA–300L, and EA–300/200 airplanes: Within the 

next 50 hours TIS after February 28, 2007 (the effective date of 

this AD). (iii) For all affected airplanes: If the modifications specified in Part II and Part III of EXTRA Service Bulletin No. 300–2–95, 

Issue: F, Dated: July 10, 2006, have already been incorporated, no 

further action is required.

Follow Part I of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 


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3052 Federal Register / Vol. 72, No. 15 / Wednesday, January 24, 2007 / Rules and Regulations 

Actions Compliance Procedures 

(2) If cracks are found during the 

inspection required in paragraph 

(e)(1) of this AD in areas A, B, 

and C (as shown in Figure 1 of 

EXTRA Service Bulletin No. 300–

2–95, Issue: F, Dated: July 10, 

2006), weld the crack and modify 

the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts).

For all affected airplanes: Before further flight after the inspection required in paragraph (e)(1) of this AD in which cracks are found, unless already done.Follow Part II of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

(3) If no cracks are found during 

the inspection required in paragraph (e)(1) of this AD, modify 

the upper longeron at the horizontal stabilizer attachment by installing the applicable modification kit (or FAA-approved equivalent parts).

For all affected airplanes: Within the next 100 hours TIS after February 28, 2007 (the effective date of this AD), unless already done.Follow Part II of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

(4) For Models EA–300S and EA–

300L airplanes only: Reinforce 

the fuselage frame underneath 

the horizontal stabilizer main spar 

attachment bracket by installing 

the applicable modification kit (or 

FAA-approved equivalent parts).

(i) For Model EA–300S: Within the next 200 hours TIS after December 17, 2002 (the effective date of AD 2002–21–11) or within the 

next 100 hours TIS after February 28, 2007 (the effective date of 

this AD), whichever occurs first, unless already done. (ii) For Model 

EA–300L: Within the next 100 hours TIS after February 28, 2007 

(the effective date of this AD), unless already done.

Follow Part III of EXTRA Service 

Bulletin No. 300–2–95, Issue: F, 

Dated: July 10, 2006. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Standards Office, Small 

Airplane Directorate, FAA, ATTN: Karl 

Schletzbaum, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4146; fax: (816) 

329–4090, 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 2002–21–11 

are approved for this AD. 

Related Information 

(h) The European Aviation Safety Agency 

(EASA) AD No. 2006–0281, dated September 

14, 2006, also addresses the subject of this 

AD. 

Material Incorporated by Reference 

(i) You must use EXTRA Service Bulletin 

No. 300–2–95, Issue: F, Dated: July 10, 2006 

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 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact EXTRA 

Flugzeugproduktions- und Vertriebs- GmbH, 

Schwarze Heide 21, D–46569 Huenxe, 

Germany; fax: (+49)–2858–9137–42. 

(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 January 

12, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–775 Filed 1–23–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24452; Directorate 

Identifier 2006–NE–11–AD; Amendment 

39–14893; AD 2007–02–06] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney PW2000 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pratt & 

Whitney PW2000 series turbofan 

engines. This AD requires a onetime 

focused visual and fluorescent penetrant 

inspection (FPI) of 21 suspect PW2000 

8th stage high pressure compressor 

(HPC) drum rotor disk assemblies. This 

AD results from a PW2037 8th stage 

HPC drum rotor disk assembly failure 

event caused by tooling damage that 

occurred during disk assembly 

manufacture. We are issuing this AD to 

prevent 8th stage HPC drum rotor disk 

assembly failure that could result in an 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective 

February 28, 2007. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of February 28, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

Pratt & Whitney, 400 Main St., East 

Hartford, CT 06108; telephone (860) 

565–8770; fax (860) 565–4503. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7758; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to Pratt & Whitney PW2000 

series turbofan engines. We published 

the proposed AD in the Federal Register 

on August 3, 2006 (71 FR 43997). That 

action proposed to require a onetime 

focused visual and FPI of 21 suspect 

PW2000 8th stage HPC drum rotor disk 

assemblies. 


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