Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46327 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6490; fax 

(425) 917–6590; has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, in the FAA Flight Standards 

District Office (FSDO), or lacking a principal 

inspector, your local FSDO. The AMOC 

approval letter must specifically reference 

this AD. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 737–27A1287, dated April 16, 2008, 

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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; e-mail me.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 or 425–227–1152. 

(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 NARA, 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 August 

31, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21412 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0397; Directorate 

Identifier 2008–NM–023–AD; Amendment 

39–16018; AD 2009–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2–1C, B2–203, B2K–3C, B4–103, 

B4–203, and B4–2C Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated 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: 

An operator has reported the loss of a 

centre flap inner tab on an in-service A300 

aircraft. The centre flap inner tab detached 

during approach to an airport. A similar 

event was reported several years ago on a 

pre-mod 04770 aircraft. * * * 

* * * Investigations led by the 

manufacturer revealed that the centre hinge 

bracket developed a fatigue crack causing 

complete failure of the bracket. The tab 

rotated causing failure of the inboard link 

followed by the failure of the outboard link. 

[D]etachment of a centre flap inner tab 

* * * could be a potential risk to persons on 

[the] ground * * *. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 30, 2009 (74 FR 

19908). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An operator has reported the loss of a 

centre flap inner tab on an in-service A300 

aircraft. The centre flap inner tab detached 

during approach to an airport. A similar 

event was reported several years ago on a 

pre-mod 04770 aircraft. Previous failure at 

the aft lug of the centre brackets led to the 

issuance of Airbus Service Bulletin A300– 

57–0205. 

In the most recent case, the aircraft had 

been modified in accordance with Airbus 

Service Bulletin A300–57–0205 (Airbus 

modification No. 04770). Investigations led 

by the manufacturer revealed that the centre 

hinge bracket developed a fatigue crack 

causing complete failure of the bracket. The 

tab rotated causing failure of the inboard link 

followed by the failure of the outboard link. 

To avoid a detachment of a centre flap 

inner tab, which could be a potential risk to 

persons on [the] ground, this AD requires a 

repetitive [high frequency eddy current] 

inspection of the centre flap inner tab hinge 

bracket and replacement of the bracket when 

cracks are detected * * * [and] reporting of 

inspection results to the TC holder [and 

provides] an optional terminating action. 

* * * 

* * * * * 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request for Clarification of Reporting 

Requirement 

TradeWinds Airlines points out that 

although paragraph (e), ‘‘Reason,’’ of the 

NPRM describes reporting inspection 

results to the Type Certificate holder, 

the requirements in paragraphs (f)(1), 

(f)(2), and (f)(3) of the NPRM currently 

have no information that describes the 

reporting requirement. 

We infer that TradeWinds Airlines is 

asking us to clarify the reporting 

requirement, and we agree that 

clarification is necessary. Paragraph (e) 

of the NPRM quotes European Aviation 

Safety Agency (EASA) AD 2007– 

0299R2, dated October 28, 2008. The 

EASA AD includes reporting; however, 

this AD does not require reporting. We 

have updated Note 1 of this final rule 

to clarify this difference. We also 

removed paragraph (g)(3) of the 


jlentini on DSKJ8SOYB1PROD with RULES
46328 Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 

proposed AD because that paragraph 

provides reporting requirement 

information and it is unnecessary to 

include that information in this final 

rule. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

22 products of U.S. registry. We also 

estimate that it will take about 55 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $96,800, or $4,400 per product. 

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 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 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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 AD: 

2009–19–01 Airbus: Amendment 39–16018. 

Docket No. FAA–2009–0397; Directorate 

Identifier 2008–NM–023–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B2–1C, B2–203, B2K–3C, B4–103, B4–203, 

and B4–2C airplanes, certificated in any 

category, all serial numbers, except airplanes 

which have been modified in accordance 

with Airbus Mandatory Service Bulletin 

A300–57–0252 (Airbus Modification 13400). 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

An operator has reported the loss of a 

centre flap inner tab on an in-service A300 

aircraft. The centre flap inner tab detached 

during approach to an airport. A similar 

event was reported several years ago on a 

pre-mod 04770 aircraft. Previous failure at 

the aft lug of the centre brackets led to the 

issuance of Airbus Service Bulletin A300– 

57–0205. 

In the most recent case, the aircraft had 

been modified in accordance with Airbus 

Service Bulletin A300–57–0205 (Airbus 

modification No. 04770). Investigations led 

by the manufacturer revealed that the centre 

hinge bracket developed a fatigue crack 

causing complete failure of the bracket. The 

tab rotated causing failure of the inboard link 

followed by the failure of the outboard link. 

To avoid a detachment of a centre flap 

inner tab, which could be a potential risk to 

persons on [the] ground, this AD requires a 

repetitive [high frequency eddy current] 

inspection of the centre flap inner tab hinge 

bracket and replacement of the bracket when 

cracks are detected * * * [and] reporting of 

inspection results to the TC holder [and 

provides] an optional terminating action. 

* * * 

* * * * * 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) At the times specified in Table 1 or 

Table 2 of this AD, as applicable, perform a 

high frequency eddy current inspection to 

detect fatigue cracks of the center hinge 

bracket of the center flap inner tab (on both 

wings), in accordance with Airbus 

Mandatory Service Bulletin A300–57–0250, 

Revision 01, dated September 29, 2008. If no 

cracking is found, repeat the inspection 

thereafter at intervals not to exceed 850 flight 

cycles. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations 46329 

TABLE 1—AIRPLANES ON WHICH AIRBUS SERVICE BULLETIN A300–57–0205 HAS NOT BEEN DONE

Flight cycles accumulated since first flight as of the effective date of 

this AD Compliance time 

Less than 6,000 flight cycles .................................................................... Prior to accumulating 6,000 flight cycles since first flight or within 90 

days after the effective date of this AD, whichever occurs later. 

6,000 flight cycles or more, but less than 12,000 flight cycles ................ Within 850 flight cycles after the effective date of this AD. 

12,000 flight cycles or more ..................................................................... Within 500 flight cycles after the effective date of this AD. 

TABLE 2—AIRPLANES ON WHICH AIRBUS SERVICE BULLETIN A300–57–0205 HAS BEEN DONE

Flight cycles accumulated since Airbus Service Bulletin A300–57–0205 

modification as of the effective date of this AD Compliance time 

Less than 6,000 flight cycles .................................................................... Prior to accumulating 6,000 flight cycles since Airbus Service Bulletin 

A300–57–0205 modification or within 90 days after the effective date 

of this AD, whichever occurs later. 

6,000 flight cycles or more, but less than 12,000 flight cycles ................ Within 850 flight cycles after the effective date of this AD. 

12,000 flight cycles or more ..................................................................... Within 500 flight cycles after the effective date of this AD. 

(2) If any crack is detected during any 

inspection required by this AD, before further 

flight, replace the center hinge bracket in the 

accordance with Airbus Mandatory Service 

Bulletin A300–57–0250, Revision 01, dated 

September 29, 2008. Within 6,000 flight 

cycles after replacing the center hinge 

bracket, do the inspection required by 

paragraph (f)(1) of this AD, and if no cracking 

is found, repeat the inspection thereafter at 

intervals not to exceed 850 flight cycles. 

(3) Modifying the inboard tab of the center 

flaps in accordance with Airbus Mandatory 

Service Bulletin A300–57–0252, dated 

August 27, 2008, terminates the requirements 

of this AD. 

(4) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Mandatory Service Bulletin A300–57– 

0250, dated November 2, 2007, are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although the European Aviation Safety 

Agency AD 2007–0299R2, dated October 28, 

2008 and Airbus Mandatory Service Bulletin 

A300–57–0250, dated November 2, 2007, 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(h) Refer to MCAI Airworthiness Directive 

2007–0299R2, dated October 28, 2008; 

Airbus Mandatory Service Bulletin A300–57– 

0250, Revision 01, dated September 29, 2008; 

and Airbus Mandatory Service Bulletin 

A300–57–0252, dated August 27, 2008; for 

related information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A300–57–0250, Revision 01, 

excluding Appendix 1, dated September 29, 

2008, to do the actions required by this AD, 

unless the AD specifies otherwise. If you do 

the optional terminating modification 

specified by this AD, you must use Airbus 

Service Bulletin A300–57–0252, dated 

August 27, 2008, to perform that action, 

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 Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail account.airwortheas@airbus.com; Internet http:// 

www.airbus.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 or 425–227–1152. 

(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 NARA, 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 August 

31, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–21411 Filed 9–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0771; Directorate 

Identifier 2009–NE–14–AD; Amendment 39– 

16009; AD 2009–18–13] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc. (RR) RB211 Trent 900 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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: 

Evidence from development testing and 

flight test Trent 900 engines has identified 

cracking on some HP Turbine Nozzle Guide 


jlentini on DSKJ8SOYB1PROD with RULES