Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 8467 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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. 

Material Incorporated by Reference 

(i) You must use Boeing Alert Service 

Bulletin MD90–53A031, dated April 10, 

2009, 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, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.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 February 

16, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3469 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0130; Directorate 

Identifier 2009–NM–087–AD; Amendment 

39–16214; AD 2010–05–05] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited Model 

ATP Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. 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: 

A review of the results of the final fuselage 

fatigue test identified the need for additional 

and revised safety-related fatigue- and 

environmental inspections for the fuselage. 

These additional tasks were introduced by 

Service Bulletin (SB) ATP–51–002 * * *. 

As it was determined that these 

inspections were necessary to maintain the 

structural integrity of the aeroplane, EASA 

AD 2006–0090 [which corresponds to FAA 

AD 2007–15–08] was issued * * *. 

Since the original Issue of the SB, three 

revisions have been published. Revision 1 of 

the SB included only editorial changes. 

Revision 2 of the SB corrected the fuselage 

frame designations in Parts 50 and 50A and 

extended the allowable time before initial 

inspection. In addition, the repeat inspection 

interval in Part 43 of the SB was reduced. In 

the latest Revision 3 of the SB, the grace 

period for the initial inspection in Part 50 has 

been clarified. 

* * * * * 

The unsafe condition is fatigue cracking 

of certain structural elements, which 

could result in reduced structural 

integrity of the airplane and consequent 

rapid decompression of the airplane. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

March 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 12, 2010. 

On September 21, 2006 (71 FR 52418, 

September 6, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in this AD. 

We must receive comments on this 

AD by April 12, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 this AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, International Branch, 

ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–1175; fax (425) 

227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 15, 2007, we issued AD 2007– 

15–08, Amendment 39–15137 (72 FR 

40230, July 24, 2007). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2007–15–08, the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0074, 

dated March 31, 2009 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

A review of the results of the final fuselage 

fatigue test identified the need for additional 

and revised safety-related fatigue- and 

environmental inspections for the fuselage. 

These additional tasks were introduced by 

Service Bulletin (SB) ATP–51–002, which 

supplemented and in some cases revised 

those previously published in the Aircraft 

Maintenance Manual (AMM) Chapter 05–10– 

17 and the Maintenance Review Board 

Report (MRBR). 

As it was determined that these 

inspections were necessary to maintain the 

structural integrity of the aeroplane, EASA 

AD 2006–0090 [which corresponds to FAA 

AD 2007–15–08] was issued to require the 

inspections and, depending on findings, 

corrective actions as defined in BAE Systems 

(Operations) Limited SB ATP–51–002 (the 

SB) at original issue. 

Since the original Issue of the SB, three 

revisions have been published. Revision 1 of 

the SB included only editorial changes. 

Revision 2 of the SB corrected the fuselage 

frame designations in Parts 50 and 50A and 

extended the allowable time before initial 


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8468 Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 

inspection. In addition, the repeat inspection 

interval in Part 43 of the SB was reduced. In 

the latest Revision 3 of the SB, the grace 

period for the initial inspection in Part 50 has 

been clarified. 

Fatigue tasks in Parts 1 through 50 of the 

SB, i.e. those without an ‘‘A’’ suffix, have now 

been replicated in AMM Chapter 05–10–17 

and MRBR Section 6. In addition, 

environmental tasks, those identified with an 

‘‘A’’ suffix, have now been replicated in 

MRBR Section 6. 

For the reasons described above, this AD 

retains the requirements of EASA AD 2006– 

0090, which is superseded, and requires the 

accomplishment of the inspections and, 

depending on findings, corrective actions as 

defined in BAE Systems (Operations) Limited 

SB ATP–51–002 at Revision 3. 

The unsafe condition is fatigue cracking 

of certain structural elements, which 

could result in reduced structural 

integrity of the airplane and consequent 

rapid decompression of the airplane. 

The corrective actions include repairing 

cracking and corrosion, and depending 

on findings, repairing or replacing 

damaged components. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

BAE SYSTEMS (Operations) Limited 

has issued Service Bulletin ATP–51– 

002, Revision 3, dated April 3, 2008. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Change to Existing AD 

This AD retains all requirements of 

AD 2007–15–08. Since AD 2007–15–08 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this AD, as listed in the 

following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2007–15–08 

Corresponding 

requirement in 

this AD 

paragraph (f) paragraph (g). 

paragraph (g) paragraph (h). 

paragraph (h) paragraph (i). 

paragraph (i) paragraph (j). 

paragraph (j) paragraph (k). 

paragraph (k) paragraph (l). 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–0130; 

Directorate Identifier 2009–NM–087– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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. 

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. 


jlentini on DSKJ8SOYB1PROD with RULES
Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 8469 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–15137 (72 FR 

40230, July 24, 2007) and adding the 

following new AD: 

2010–05–05 BAE Systems (Operations) 

Limited: Amendment 39–16214. Docket 

No. FAA–2010–0130; Directorate 

Identifier 2009–NM–087–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 12, 2010. 

Affected ADs 

(b) This AD supersedes AD 2007–15–08, 

Amendment 39–15137. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model ATP airplanes, 

certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new and revised 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 damage tolerance 

of the affected structure. The FAA has 

provided guidance for this determination in 

Advisory Circular (AC) 25–1529. 

Subject 

(d) Air Transport Association (ATA) of 

America Code: 51: Standard Practices/ 

Procedures. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

A review of the results of the final fuselage 

fatigue test identified the need for additional 

and revised safety-related fatigue- and 

environmental inspections for the fuselage. 

These additional tasks were introduced by 

Service Bulletin (SB) ATP–51–002, which 

supplemented and in some cases revised 

those previously published in the Aircraft 

Maintenance Manual (AMM) Chapter 05–10– 

17 and the Maintenance Review Board 

Report (MRBR). 

As it was determined that these 

inspections were necessary to maintain the 

structural integrity of the aeroplane, EASA 

AD 2006–0090 [which corresponds to FAA 

AD 2007–15–08] was issued to require the 

inspections and, depending on findings, 

corrective actions as defined in BAE Systems 

(Operations) Limited SB ATP–51–002 (the 

SB) at original issue. 

Since the original Issue of the SB, three 

revisions have been published. Revision 1 of 

the SB included only editorial changes. 

Revision 2 of the SB corrected the fuselage 

frame designations in Parts 50 and 50A and 

extended the allowable time before initial 

inspection. In addition, the repeat inspection 

interval in Part 43 of the SB was reduced. In 

the latest Revision 3 of the SB, the grace 

period for the initial inspection in Part 50 has 

been clarified. 

Fatigue tasks in Parts 1 through 50 of the 

SB, i.e. those without an ‘‘A’’ suffix, have now 

been replicated in AMM Chapter 05–10–17 

and MRBR Section 6. In addition, 

environmental tasks, those identified with an 

‘‘A’’ suffix, have now been replicated in 

MRBR Section 6. 

For the reasons described above, this AD 

retains the requirements of EASA AD 2006– 

0090, which is superseded, and requires the 

accomplishment of the inspections and, 

depending on findings, corrective actions as 

defined in BAE Systems (Operations) Limited 

SB ATP–51–002 at Revision 3. 

The unsafe condition is fatigue cracking of 

certain structural elements, which could 

result in reduced structural integrity of the 

airplane and consequent rapid 

decompression of the airplane. The 

corrective actions include repairing cracking 

and corrosion, and depending on findings, 

repairing or replacing damaged components. 

Compliance 

(f) 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– 

18–09, With Revised Compliance Method 

Airworthiness Limitations Revision 

Specified in AD 2000–26–10 

(g) Within 30 days after February 7, 2001 

(the effective date of AD 2000–26–10, 

Amendment 39–12060, which was 

superseded by AD 2005–19–03, which was 

superseded by AD 2007–15–08), revise the 

Airworthiness Limitations Section (ALS) of 

the Instructions for Continued Airworthiness 

according to a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. Doing 

the revision specified in paragraph (h) of this 

AD replaces Chapters 27, 32, 53, and 54 

listed in Section 05–10–11 and Chapters 52, 

53, 54, 55, and 57 listed in Section 05–10– 

17 that are in effect on February 7, 2001, with 

Chapters 27, 32, 53, and 54 listed in Section 

05–10–11, ‘‘Mandatory Life Limitations 

(Airframe)’’; and Chapters 52, 53, 54, 55, and 

57 listed in Section 05–10–17, ‘‘Structurally 

Significant Items (SSIs)’’; both dated July 15, 

2004; of the British Aerospace ATP Aircraft 

Maintenance Manual (AMM). Doing the 

revision specified in paragraph (l) of this AD 

replaces Sections 05–10–12, 05–10–15, and 

05–10–17 with the corresponding sections 

specified in paragraph (l) of this AD. 

Note 2: Guidance on revising the ALS can 

be found in Section 05–00–00, dated August 

15, 1997, of the British Aerospace ATP 

AMM, dated October 15, 1999. This section 

references other chapters of the AMM. The 

applicable revision level of the referenced 

chapters is that in effect on February 7, 2001. 

Airworthiness Limitations Specified in AD 

2005–19–03 

(h) Within 30 days after September 28, 

2005 (the effective date of AD 2005–19–03, 

Amendment 39–14268, which was 

superseded by AD 2006–18–09), revise the 

ALS of the Instructions for Continued 

Airworthiness according to a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. Doing the revision 

specified in paragraph (i) of this AD replaces 

certain Chapter 52 and 53 tasks listed in 

Section 05–10–17, ‘‘Structurally Significant 

Items (SSIs),’’ dated July 15, 2004, of the 

British Aerospace ATP AMM, with the 

corresponding Chapter 52 and 53 tasks listed 

in BAE SYSTEMS (Operations) Limited 

Service Bulletin ATP–51–002, dated 

December 20, 2005. Doing the revision 

specified in paragraph (l) of this AD replaces 

Chapters 52, 53, 54, 55, and 57 listed in 

Section 05–10–17 with the corresponding 

Section 05–10–17 specified in paragraph (l) 

of this AD. 

Note 3: Guidance on revising the ALS can 

be found in Chapters 27, 32, 53, and 54 listed 

in Section 05–10–11, ‘‘Mandatory Life 

Limitations (Airframe)’’; and the tasks for 

Chapters 52, 53, 54, 55, and 57 listed in 

Section 05–10–17, ‘‘Structurally Significant 

Items (SSIs)’’; both dated July 15, 2004; of the 

British Aerospace ATP AMM. These chapters 

replace the corresponding chapters in 

Section 05–00–00, dated August 15, 1997, of 

the British Aerospace ATP AMM as specified 

in paragraph (g) of this AD. 

New and Revised Airworthiness Limitations 

in AD 2006–18–09 

(i) Within 30 days after September 21, 2006 

(the effective date of AD 2006–18–09), revise 

the ALS of the Instructions for Continued 

Airworthiness by incorporating the new and 

revised tasks for Chapters 52 and 53 as 

specified in BAE SYSTEMS (Operations) 

Limited Service Bulletin ATP–51–002, dated 

December 20, 2005, into the ALS. The 

revised Chapter 52 and 53 tasks replace the 

corresponding Chapter 52 and 53 tasks in 

Section 05–10–17, ‘‘Structurally Significant 

Items (SSIs),’’ dated July 15, 2004, of the 

British Aerospace ATP AMM, as specified in 

paragraph (h) of this AD. 

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

this AD: After the actions specified in 

paragraphs (g), (h), and (i) of this AD have 

been accomplished, no alternative 

inspections or inspection intervals may be 

approved for the structural elements 

specified in the documents listed in 

paragraphs (g), (h), and (i) of this AD. 

No Reporting Required 

(k) Although BAE SYSTEMS (Operations) 

Limited Service Bulletin ATP–51–002, dated 

December 20, 2005, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Restatement of Requirements of AD 2007– 

15–08, With Revised Compliance Method 

Revised Limitations 

(l) Within 30 days after August 8, 2007 (the 

effective date of AD 2007–15–08), revise the 


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ALS of the Instructions for Continued 

Airworthiness according to a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. 

Note 4: Guidance on revising the ALS can 

be found in Section 05–10–12, ‘‘Mandatory 

Life Limitations (Airframe—Structures),’’ 

dated January 15, 2007; Section 05–10–15, 

‘‘Mandatory Life Limitations (Powerplant/ 

Engine/APU—Structures),’’ dated January 15, 

2007; and Section 05–10–17, ‘‘Structurally 

Significant Items (SSIs),’’ dated January 15, 

2007; of the BAE Systems (Operations) 

Limited ATP AMM. The revised sections 

replace the corresponding sections specified 

in paragraphs (g) and (h) of this AD. 

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

this AD: After the action specified in 

paragraph (l) of this AD has been 

accomplished, no alternative inspections or 

inspection intervals may be approved for the 

structural elements specified in the 

documents listed in paragraph (l) of this AD. 

New Requirements of This AD 

Actions 

(n) Within 30 days after the effective date 

of this AD: Revise the ALS of the Instructions 

for Continued Airworthiness by 

incorporating the inspections specified in 

BAE SYSTEMS (Operations) Limited 

Inspection Service Bulletin ATP–51–002, 

Revision 3, dated April 3, 2008. Doing this 

revision terminates the requirements of 

paragraph (i) of this AD. The revised Chapter 

52 and 53 tasks replace the corresponding 

Chapter 52 and 53 tasks in Section 05–10– 

17, ‘‘Structurally Significant Items (SSIs),’’ 

dated July 15, 2004, of the British Aerospace 

ATP AMM, as specified in paragraph (h) of 

this AD. Do the initial inspection for fatigue 

cracking at the applicable time in Part N., 

‘‘Approval,’’ of BAE SYSTEMS (Operations) 

Limited Inspection Service Bulletin ATP–51– 

002, Revision 3, dated April 3, 2008. 

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

this AD: After the action specified in 

paragraph (n) of this AD has been 

accomplished, no alternative inspections or 

inspection intervals may be approved for the 

structural elements specified in the 

documents listed in paragraph (n) of this AD. 

(p) Submit a report of the findings (both 

positive and negative) of all of the 

inspections required by paragraph (n) of this 

AD to Customer Engineering Liaison, BAE 

SYSTEMS Regional Aircraft, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland; telephone: +44 (0) 1292 675289; 

fax: +44 (0) 1292 675432; at the applicable 

time specified in paragraph (p)(1) or (p)(2) of 

this AD. The report must include the 

inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of landings and 

flight hours on the airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(q) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: Todd Thompson, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1175; 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. The AMOC approval letter must 

specifically reference this AD. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(r) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2009–0074, dated 

March 31, 2009; and BAE SYSTEMS 

(Operations) Limited Inspection Service 

Bulletin ATP–51–002, Revision 3, dated 

April 3, 2008; for related information. 

Material Incorporated by Reference 

(s) You must use the service information 

contained in Table 1 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 .................................... 3 ................................ April 3, 2008. 

BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 .................................... Original ...................... December 20, 2005. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 2 

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

part 51. 

TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 ................................................ 3 April 3, 2008. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 3 of this AD on September 

21, 2006 (71 FR 52418, September 6, 2006). 

TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Document Revision Date 

BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 .................................... Original ...................... December 20, 2005. 


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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations 8471 

(3) For service information identified in 

this AD, contact BAE SYSTEMS Regional 

Aircraft, 13850 McLearen Road, Herndon, 

Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(4) 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. 

(5) 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 February 

16, 2010. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–3470 Filed 2–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0131; Directorate 

Identifier 2009–NM–132–AD; Amendment 

39–16216; AD 2010–05–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–200 and A340–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

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: 

A review of A340 missions has 

demonstrated that CFM56–5C forward engine 

mount thrust links fitted with oversized 

bearing[s] will not reach the updated link 

fatigue life limit of 15500 Flight Cycles (FC) 

due to an increase in bore diameter. 

* * * The consequent potential failure of 

the affected thrust link would reduce the 

forward engine mounts’ structural integrity 

and could eventually lead to engine 

separation, constituting an unsafe condition. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

March 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 12, 2010. 

We must receive comments on this 

AD by April 12, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 this AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0108, 

dated May 5, 2009 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

A review of A340 missions has 

demonstrated that CFM56–5C forward engine 

mount thrust links fitted with oversized 

bearing[s] will not reach the updated link 

fatigue life limit of 15,500 Flight Cycles (FC) 

due to an increase in bore diameter. 

Oversized bearing repairs have been 

possible through the accomplishment of 

CMM 71–21–12 Repair 1. The consequent 

potential failure of the affected thrust link 

would reduce the forward engine mounts’ 

structural integrity and could eventually lead 

to engine separation, constituting an unsafe 

condition. 

Consequently, this AD requires: 

—The [detailed] inspection of the link 

assembly to identify a possible oversized 

bearing repair and, in case of finding, the 

application of the associated corrective 

actions, or 

—The repetitive [detailed] inspection [for 

cracking, damage (e.g., dents), and missing 

fasteners] of the forward engine mounts 

until accomplishment of the inspection of 

the link assembly for the identification of 

a possible oversized bearing repair. 

The corrective actions for finding 

oversized bearings in the forward engine 

mount thrust link assembly include 

contacting Goodrich for instructions and 

doing the repair. The corrective actions 

for finding cracking, damage (e.g., 

dents), and missing fasteners in the 

forward engine mounts include, 

depending on the findings, replacing 

cracked parts and missing fasteners, and 

polishing damaged areas. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–71–4007, including 

Appendix 1, dated April 1, 2009. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 


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