12228 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

(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 Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.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. 

TABLE 4—SERVICE BULLETINS INCORPORATED BY REFERENCE

Bombardier Service Bulletin— Revision— Dated— 

600–0734 ........................................................................................ Original ....................................................................... November 30, 2006. 

601–0585 ........................................................................................ Original ....................................................................... November 30, 2006. 

604–30–003 .................................................................................... 01 ............................................................................... January 21, 2008. 

TABLE 5—TEMPORARY REVISIONS INCORPORATED BY REFERENCE

Canadair TR— Dated— To the— 

600/23 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM. 

600–1/19 ......................................... August 16, 2006 ............................ Canadair Challenger Model CL–600–1A11 AFM (Winglets). 

601/14 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B–1. 

601/15 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1A–1. 

601/19 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM, PSP 601–1B. 

601/26 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1. 

601/27 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–2A12 AFM. 

601/27 ............................................. August 16, 2006 ............................ Canadair Challenger Model CL–600–2B16 AFM, PSP 601A–1–1. 

604/20 ............................................. April 17, 2006 ................................ Canadair Challenger Model CL–604 AFM, PSP 604–1. 

Issued in Renton, Washington, on February 

27, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5968 Filed 3–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0018; Directorate 

Identifier 2007–NM–145–AD; Amendment 

39–15842; AD 2009–06–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes and Model 

A300–600 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: This airworthiness directive 

(AD) supersedes two existing ADs. One 

AD applies to certain Airbus Model 

A310–200 and –300 series airplanes. 

That AD currently requires repetitive 

inspections for cracking of the flap 

transmission shafts, and replacement of 

the transmission shafts if necessary. 

That AD also provides an optional 

terminating action for the repetitive 

inspections. The other existing AD 

applies to all Airbus Model A300 B4– 

600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R Variant F 

airplanes (collectively called A300–600 

series airplanes); and Model A310–200 

and –300 series airplanes. That AD 

currently requires a one-time inspection 

of the trimmable horizontal stabilizer 

actuator (THSA), corrective actions if 

necessary, and follow-on repetitive 

tasks. This new AD also requires 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness to incorporate 

new limitations and maintenance tasks 

for aging systems maintenance. This AD 

results from the manufacturer’s 

determination that life limitations and 

maintenance tasks are necessary to 

ensure continued operational safety of 

the affected airplanes. We are issuing 

this AD to prevent reduced structural 

integrity of these airplanes due to the 

failure of system components. 

DATES: This AD becomes effective April 

28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 28, 2009. 

On August 29, 2006 (71 FR 42021, 

July 25, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of Airbus 

Service Bulletin A300–27–6044, 

Revision 04, dated September 10, 2001; 

and Airbus Service Bulletin A310–27– 

2089, Revision 02, dated June 28, 2001. 

On June 20, 2006 (71 FR 28254, May 

16, 2006), the Director of the Federal 

Register approved the incorporation by 

reference of Airbus Service Bulletin 

A310–27–2092, Revision 02, dated April 

11, 2005; and Airbus Service Bulletin 

A310–27–2095, dated March 29, 2000. 

ADDRESSES: For Airbus 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.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For 

TRW Aeronautical Systems service 

information identified in this AD, 

contact TRW Syste`mes Ae ́ronautiques 

Civils SAS, Product Support 

Department, 7–9 Avenue de l’Eguillette, 

Saint Ouen l’Aumone BP 7186, 95056 

Cergy-Pontoise Cedex France, telephone 

+33 1 34 32 63 00; fax +33 1 34 32 63 

10. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 regulatory 

evaluation, any comments received, and 

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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 12229 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the 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: 

Thomas Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1622; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that supersedes two existing ADs: 

AD 2006–10–11, amendment 39–14595 

(71 FR 28254, May 16, 2006); and AD 

2006–15–10, amendment 39–14690 (71 

FR 42021, July 25, 2006). AD 2006–10– 

11 applies to certain Airbus Model 

A310–200 and –300 series airplanes and 

requires repetitive inspections for 

cracking of the flap transmission shafts, 

and replacing the transmission shafts if 

necessary. That existing AD also 

provides an optional terminating action 

for the repetitive inspections. AD 2006– 

15–10 applies to all Airbus Model A310 

and A300–600 series airplanes and 

requires a one-time inspection of the 

trimmable horizontal stabilizer actuator 

(THSA), corrective actions if necessary, 

and follow-on repetitive tasks. 

That supplemental NPRM was 

published in the Federal Register on 

September 26, 2008 (73 FR 55781). That 

supplemental NPRM proposed to 

continue to require the actions required 

by the two existing ADs. That 

supplemental NPRM also proposed to 

require revising the Airworthiness 

Limitations Section of the Instructions 

for Continued Airworthiness to 

incorporate new limitations and 

maintenance tasks for aging systems 

maintenance. In addition, that 

supplemental NPRM proposed to revise 

the original NPRM by reducing the 

initial compliance times. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the supplemental 

NPRM or on the determination of the 

cost to the public. 

Explanation of Changes 

We have removed the ‘‘Service 

Bulletin References’’ paragraph in the 

‘‘RESTATEMENT OF REQUIREMENTS 

OF AD 2006–15–10’’ section of this AD. 

Instead, we refer to the required service 

documents in the individual paragraphs 

of this AD. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the changes 

described previously. We also 

determined that these changes will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Cost per airplane 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Inspection (required by AD 

2006–10–11).

1 $80 $80 per inspection cycle ........... 59 $4,720 per inspection cycle. 

Inspection (required by AD 

2006–15–10).

3 80 $240 .......................................... 213 $51,120. 

Repetitive follow-on tasks (required by AD 2006–15–10).12 80 $960 per inspection cycle ......... 213 $204,480 per inspection cycle. 

ALS revision (new action) ......... 1 80 $80 ............................................ 213 $17,040. 

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); 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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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: 

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12230 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14595 (71 

FR 28254, May 16, 2006), and 

amendment 39–14690 (71 FR 42021, 

July 25, 2006), and by adding the 

following new airworthiness directive 

(AD): 

2009–06–06 Airbus: Amendment 39–15842. 

Docket No. FAA–2008–0018; Directorate 

Identifier 2007–NM–145–AD. 

Effective Date 

(a) This AD becomes effective April 28, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2006–10–11 

and AD 2006–15–10. 

Applicability 

(c) This AD applies to all Airbus Model 

A310 series airplanes; and Model A300–600 

series airplanes; certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (q) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Unsafe Condition 

(d) This AD results from the 

manufacturer’s determination that life 

limitations and maintenance tasks are 

necessary to ensure continued operational 

safety of the affected airplanes. We are 

issuing this AD to prevent reduced structural 

integrity of these airplanes due to the failure 

of system components. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

10–11 

Inspection and Corrective Action 

(f) For Airbus Model A310–203, –204, 

–221, –222, –304, –322, –324, and –325 

airplanes, except for airplanes on which 

Airbus Modification 12247 has been 

embodied in production: At the earlier of the 

compliance times specified in paragraph 

(f)(1) or (f)(2) of this AD, perform a detailed 

inspection for stress corrosion cracking of the 

flight transmission shafts located between the 

power control unit (PCU) and the torque 

limiters in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–27–2092, Revision 02, 

dated April 11, 2005. Thereafter, repeat the 

inspections as required by paragraph (g) of 

this AD. Before further flight, replace any 

cracked transmission shaft discovered during 

any inspection required by this AD with a 

new or reconditioned shaft, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A310–27–2095, 

dated March 29, 2000. Doing an inspection 

in accordance with paragraph (n) or (o) of 

this AD terminates the requirements of this 

paragraph. 

(1) Within 2,000 flight hours after the last 

flap asymmetry protection test performed in 

accordance with Airbus A310 Maintenance 

Planning Document (MPD) Task 275600–01– 

1. 

(2) Within 8,000 flight cycles after the last 

flap asymmetry protection test performed in 

accordance with Airbus A310 MPD Task 

275600–02–1 or 800 flight cycles after June 

20, 2006 (the effective date of AD 2006–10– 

11), whichever comes later. 

Note 2: Airbus Service Bulletin A310–27– 

2092, Revision 02, dated April 11, 2005, 

refers to Lucas Liebherr Service Bulletin 

551A–27–624, Revision 1, dated August 18, 

2000, as a source of service information for 

accomplishing the inspections. 

Note 3: Airbus Service Bulletin A310–27– 

2092, Revision 02, dated April 11, 2005, 

refers to Airbus Service Bulletin A310–27– 

2095, dated March 29, 2000, as a source of 

information for replacing the flap 

transmission shafts. 

Note 4: Airbus Service Bulletin A310–27– 

2095, dated March 29, 2000, refers to Lucas 

Liebherr Service Bulletin 551A–27–M551– 

05, dated January 12, 2000, as an additional 

source of information for replacing the flap 

transmission shafts. 

Repetitive Inspections 

(g) Repeat the inspection required by 

paragraph (f) of this AD at the applicable 

times specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD. Doing an inspection in 

accordance with paragraph (n) or (o) of this 

AD terminates the requirements of this 

paragraph. 

(1) Before further flight after any 

occurrence of jamming of the flap 

transmission system. 

(2) At intervals not to exceed 2,000 flight 

hours after each flap asymmetry protection 

test performed in accordance with Airbus 

A310 MPD Task 275600–01–1. 

(3) At intervals not to exceed 8,000 flight 

cycles after each flap asymmetry protection 

test performed in accordance with Airbus 

A310 MPD Task 275600–02–1. 

Optional Terminating Action 

(h) Replacing any flap transmission shaft 

with a new or reconditioned transmission 

shaft in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–27–2095, dated March 

29, 2000, ends the inspections required by 

paragraphs (f) and (g) of this AD for that 

transmission shaft only. 

Actions Performed Using Previously Issued 

Service Information 

(i) Actions performed in accordance with 

Airbus Service Bulletin A310–27–2092, 

dated April 9, 1999; or Revision 01, dated 

December 11, 2001; are considered 

acceptable for compliance with the 

corresponding requirements of paragraphs (f) 

and (g) of this AD. 

No Reporting 

(j) Although Airbus Service Bulletin A310– 

27–2092, Revision 02, dated April 11, 2005, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Restatement of Requirements of AD 2006– 

15–10 

Inspection 

(k) At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD, do a 

detailed inspection of specified components 

of the trimmable horizontal stabilizer 

actuator (THSA) in accordance with 

paragraph 1.E.(2)(a) and the Accomplishment 

Instructions of the applicable service bulletin 

as identified in Table 1 of this AD. Repair 

any discrepancy before further flight in 

accordance with TRW Aeronautical Systems 

Horizontal Stabilizer Actuator 47142 Series 

Component Maintenance Manual with 

Illustrated Parts List 27–44–13, Revision 6, 

dated September 14, 2001; or a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or the European Aviation 

Safety Agency (EASA) (or its delegated 

agent). Doing an inspection in accordance 

with paragraph (n) or (o) of this AD 

terminates the requirements of this 

paragraph. 

(1) If the flight hours accumulated on the 

THSA can be positively determined: Inspect 

at the earlier of: 

(i) Before the accumulation of 47,000 total 

flight hours on the THSA, or within 600 

flight hours after August 29, 2006 (the 

effective date of AD 2006–15–10), whichever 

occurs later. 

(ii) Within 25 years since the THSA was 

new or within 600 flight hours after August 

29, 2006, whichever occurs later. 

(2) If the flight hours accumulated on the 

THSA cannot be positively determined: 

Inspect before the accumulation of 47,000 

total flight hours on the airplane, or within 

600 flight hours after August 29, 2006, 

whichever occurs later. 

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TABLE 1—SERVICE BULLETINS FOR THE REQUIREMENTS OF PARAGRAPH (k) OF THIS AD 

Required Airbus Service Bulletin 

Approved Airbus Service Bulletin version 

for actions done before the effective date 

of this AD 

Airbus airplane model 

Airbus Service Bulletin A300–27–6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300–27– 

6044, Revision 05, dated August 29, 2006.

A300–27–6044, Revision 02, dated August 

26, 2000; or Revision 03, dated June 28, 

2001.

A300 B4–601, B4–603, B4–620, and B4–622. 

A300 B4–605R and B4–622R. 

A300 B4–605R and B4–622R. 

A300 C4–605R Variant F. 

Airbus Service Bulletin A310–27–2089, Revision 02, dated June 28, 2001; or Airbus 

Mandatory Service Bulletin A310–27–2089, 

Revision 03, dated August 29, 2006.

........................................................................... A310–203, –204, –221, and –222. 

A310–304, –322, –324, and –325. 

Note 5: The service bulletins specified in 

Table 1 of this AD refer to Goodrich 

Actuation Systems Service Bulletin 47142– 

27–11, Revision 3, dated April 25, 2005, as 

an additional source of service information 

for the required actions. 

Note 6: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Follow-on Repetitive Tasks 

(l) After the inspection required by 

paragraph (k) of this AD: Do the repetitive 

tasks in accordance with the 

Accomplishment Instructions and at the 

times specified in paragraph 1.E.(2)(b) of the 

applicable service bulletin identified in Table 

2 of this AD, except as provided by paragraph 

(m) of this AD. The repetitive tasks are valid 

only until the THSA operational life exceeds 

65,000 flight hours, 40,000 flight cycles, or 25 

years, whichever occurs first. Before the 

THSA is operated beyond these extended life 

goals, it must be replaced with a new or 

serviceable THSA, except as required by 

paragraph (m) of this AD. Doing an 

inspection in accordance with paragraph (n) 

or (o) of this AD terminates the requirements 

of this paragraph. 

TABLE 2—SERVICE BULLETINS FOR THE REQUIREMENTS OF PARAGRAPH (L) OF THIS AD 

Required Airbus Service Bulletin 

Approved Airbus Service Bulletin version 

for actions done before the effective date 

of this AD 

Airbus airplane model 

Airbus Service Bulletin A300–27–6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300–27– 

6044, Revision 05, dated August 29, 2006.

A300–27–6044, Revision 02, dated August 

26, 2000; or Revision 03, dated June 28, 

2001.

A300 B4–601, B4–603, B4–620, and B4–622. 

A300 B4–605R and B4–622R. 

A300 B4–605R and B4–622R. 

A300 C4–605R Variant F. 

Airbus Service Bulletin A310–27–2089, Revision 02, dated June 28, 2001; or Airbus 

Mandatory Service Bulletin A310–27–2089, 

Revision 03, dated August 29, 2006.

A310–27–2089, Revision 01, dated August 

25, 2000.

A310–203, –204, –221, and –222. 

A310–304, –322, –324, and –325. 

Note 7: For additional information on the 

THSA life limits, refer to Airbus Operators 

Information Telex (OIT) SE 999.0074/05/BB, 

dated August 3, 2005. 

THSA Replacement 

(m) For any THSA, whether discrepant or 

not, that is replaced with a new or 

serviceable THSA: Within 47,000 flight hours 

or 25 years, whichever occurs first, after the 

THSA is replaced, do the applicable tasks 

specified in paragraph 1.E.(2)(a) and the 

Accomplishment Instructions of the 

applicable service bulletin identified in Table 

3. Thereafter repeat the tasks within the 

repetitive intervals specified in paragraph 

1.E.(2)(b) of the applicable service bulletin. 

Doing the corresponding tasks in accordance 

with paragraph (n) or (o) of this AD 

terminates the requirements of this 

paragraph. 

TABLE 3—SERVICE BULLETINS FOR THE REQUIREMENTS OF PARAGRAPH (m) OF THIS AD 

Required Airbus Service Bulletin 

Approved Airbus Service Bulletin version 

for actions done before the effective date 

of this AD 

Airbus airplane model 

Airbus Service Bulletin A300–27–6044, Revision 04, dated September 10, 2001; or Airbus Mandatory Service Bulletin A300–27– 

6044, Revision 05, dated August 29, 2006.

A300–27–6044, Revision 02, dated August 

26, 2000; or Revision 03, dated June 28, 

2001.

A300 B4–601, B4–603, B4–620, and B4–622. 

A300 B4–605R and B4–622R. 

A300 F4–605R and F4–622R. 

A300 C4–605R Variant F. 

Airbus Service Bulletin A310–27–2089, Revision 02, dated June 28, 2001; or Airbus 

Mandatory Service Bulletin A310–27–2089, 

Revision 03, dated August 29, 2006.

A310–27–2089, Revision 01, dated August 

25, 2000.

A310–203, –204, –221, and –222. 

A310–304, –322, –324, and –325. 

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12232 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

New Requirements of This AD 

Revise Airworthiness Limitations Section 

(ALS) To Incorporate Limitations and 

Maintenance Tasks for Aging Systems 

Maintenance 

(n) Within 3 months after the effective date 

of this AD, revise the ALS of the Instructions 

for Continued Airworthiness (ICA) to 

incorporate Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006 (for Model A310 series 

airplanes); or Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 01, 

dated December 21, 2006 (for Model A300– 

600 series airplanes). For all tasks identified 

in Airbus A310 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

21, 2006; and Airbus A300–600 ALS Part 4— 

Ageing Systems Maintenance, Revision 01, 

dated December 21, 2006; do the tasks at the 

later of the times specified in paragraphs 

(n)(1) and (n)(2) of this AD, as applicable, 

except as provided by paragraph (o) of this 

AD. The repetitive inspections must be 

accomplished thereafter at the interval 

specified in Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006; or Airbus A300–600 ALS 

Part 4—Ageing Systems Maintenance, 

Revision 01, dated December 21, 2006; as 

applicable. Doing an inspection required by 

this paragraph terminates the corresponding 

inspection required by paragraph (f), (g), (k), 

(l), or (m) of this AD. 

(1) At the initial compliance times 

(thresholds) specified in Airbus A310 ALS 

Part 4—Ageing Systems Maintenance, 

Revision 01, dated December 21, 2006; or 

Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006; as applicable; with the 

compliance times starting from the later of 

the times specified in paragraphs (n)(1)(i) and 

(n)(1)(ii) of this AD. 

(i) Since first flight of the airplane. 

(ii) Since the applicable part was new or 

refurbished if the part’s life (in flight hours, 

flight cycles, landings, or calendar time, as 

applicable) can be conclusively determined. 

(2) Within 3 months after doing the 

revision of the ALS of the ICA required by 

paragraph (o) of this AD. 

Note 8: For additional information on the 

THSA life limits, refer to Airbus OIT SE 

999.0074/05/BB, dated August 3, 2005. 

Note 9: For additional information on the 

THSA life limits and calculation method for 

unknown history of parts, refer to Airbus OIT 

SE 999.0008/07/LB, dated January 16, 2007; 

and Airbus Service Information Letter 05– 

008, Revision 01, dated February 21, 2007. 

(o) For airplanes on which any life 

limitation/maintenance task has been 

complied with in accordance with the 

requirements of paragraph (f), (g), (k), (l), or 

(m) of this AD (e.g., AD 2006–10–11 or AD 

2006–15–10), the last accomplishment of 

each limitation/task must be retained as a 

starting point for the accomplishment of each 

corresponding limitation/task interval now 

introduced in Airbus A310 ALS Part 4— 

Ageing Systems Maintenance, Revision 01, 

dated December 21, 2006; and Airbus A300– 

600 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

21, 2006; as applicable. Doing an inspection 

required by this paragraph terminates the 

corresponding inspection required by 

paragraph (f), (g), (k), (l), or (m) of this AD. 

(p) Except as provided by paragraph (q) of 

this AD: After accomplishing the actions 

specified in paragraphs (n) and (o) of this AD, 

no alternative inspection, inspection 

intervals, or limitations may be used. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(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. Send information to 

ATTN: Thomas Stafford, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1622; fax (425) 

227–1149. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) AMOCs approved previously in 

accordance with AD 2006–10–11 are not 

approved as AMOCs with this AD. 

(3) AMOCs approved previously in 

accordance with AD 2006–15–10 are not 

approved as AMOCs with this AD. 

Related Information 

(r) EASA airworthiness directive 2007– 

0092, dated April 10, 2007, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(s) You must use the service information 

identified in Table 4 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. If you 

accomplish the optional actions specified by 

this AD, you must use Airbus Service 

Bulletin A310–27–2095, dated March 29, 

2000, to perform those actions, unless the AD 

specifies otherwise. 

TABLE 4—MATERIAL INCORPORATED BY REFERENCE FOR THE ACTIONS REQUIRED BY THIS AD 

Document Revision Date 

Airbus A300–600 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ... 01 ................ December 21, 2006. 

Airbus A310 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ........... 01 ................ December 21, 2006. 

Airbus Mandatory Service Bulletin A300–27–6044 .............................................................................. 05 ................ August 29, 2006. 

Airbus Mandatory Service Bulletin A310–27–2089 .............................................................................. 03 ................ August 29, 2006. 

Airbus Service Bulletin A300–27–6044 ................................................................................................ 04 ................ September 10, 2001. 

Airbus Service Bulletin A310–27–2089 ................................................................................................ 02 ................ June 28, 2001. 

Airbus Service Bulletin A310–27–2092 ................................................................................................ 02 ................ April 11, 2005. 

Airbus Service Bulletin A310–27–2095 ................................................................................................ Original ........ March 29, 2000. 

TRW Aeronautical Systems Horizontal Stabilizer Actuator 47142 Series Component Maintenance 

Manual with Illustrated Parts List 27–44–13.

6 .................. September 14, 2001. 

(TRW Aeronautical Systems Horizontal 

Stabilizer Actuator 47142 Series Component 

Maintenance Manual with Illustrated Parts 

List 27–44–13 contains the following 

discrepancies: The revision level of the 

document is only specified on the Letter of 

Transmittal; the Letter of Transmittal is not 

specified in the List of Effective Pages; and 

the List of Effective Pages refers to page 748a 

as 748b.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 5 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 5—NEW MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus A300–600 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ... 01 ................ December 21, 2006. 

Airbus A310 Airworthiness Limitations Section (ALS) Part 4—Ageing Systems Maintenance ........... 01 ................ December 21, 2006. 

Airbus Mandatory Service Bulletin A300–27–6044 .............................................................................. 05 ................ August 29, 2006. 

Airbus Mandatory Service Bulletin A310–27–2089 .............................................................................. 03 ................ August 29, 2006. 

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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 12233 

TABLE 5—NEW MATERIAL INCORPORATED BY REFERENCE—Continued 

Document Revision Date 

TRW Aeronautical Systems Horizontal Stabilizer Actuator 47142 Series Component Maintenance 

Manual with Illustrated Parts List 27–44–13.

Original ........ September 14, 2001. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 6 of this AD on August 

29, 2006 (71 FR 42021, July 25, 2006). 

TABLE 6—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2006–15–10 

Document Revision Date 

Airbus Service Bulletin A300–27–6044 .............................................................................................. 04 September 10, 2001. 

Airbus Service Bulletin A310–27–2089 .............................................................................................. 02 June 28, 2001. 

(3) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 7 of this AD on June 20, 

2006 (71 FR 28254, May 16, 2006). 

TABLE 7—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2006–10–11 

Document Revision Date 

Airbus Service Bulletin A310–27–2092 ................................................................................................ 02 ................ April 11, 2005. 

Airbus Service Bulletin A310–27–2095 ................................................................................................ Original ........ March 29, 2000. 

(4) For Airbus 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. 

(5) For TRW Aeronautical Systems service 

information identified in this AD, contact 

TRW Syste ́mes Aeacute;ronautiques Civils 

SAS, Product Support Department, 7–9 

Avenue de l’Eguillette, Saint Ouen l’Aumone 

BP 7186, 95056 Cergy-Pontoise Cedex 

France, telephone +33 1 34 32 63 00; fax +33 

1 34 32 63 10. 

(6) 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. 

(7) You may also review copies of the 

service information 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 February 

27, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5969 Filed 3–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0668; Directorate 

Identifier 2008–NM–088–AD; Amendment 

39–15847; AD 2009–06–11] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 190 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: 

During aircraft structure fatigue tests, 

cracks were found in the wing lower skin 

stringers between ribs 7 and 10 on both 

wings. In order to prevent fatigue cracks in 

the wing lower skin stringers, which could 

result in fuel leakage and reduced structural 

integrity of the wing, the referred stringers 

must be reworked. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 28, 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: 

Kenny Kaulia, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2848; 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 June 24, 2008 (73 FR 35597). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

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