Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 20515 

(l) Concurrent Actions for Paragraph (i) of 

This AD 

For airplanes identified in Boeing Service 

Bulletin 737–78–1069, Revision 4, dated June 

16, 2005: Before or concurrently with the 

accomplishment of the requirements of 

paragraph (i) of this AD, modify the thrust 

reverser inner wall and insulation blankets, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

78–1069, Revision 4, dated June 16, 2005. 

This paragraph provides credit for the actions 

specified in Boeing Service Bulletin 737–78– 

1069, Revision 4, dated June 16, 2005, if 

those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 737–78–1069, Revision 1, dated June 

13, 2002; Revision 2, dated February 6, 2003; 

or Revision 3, dated August 5, 2004. 

(m) Concurrent Actions for Paragraph (i) of 

This AD Done Before the Compliance Time 

for paragraph (g) of This AD 

If the actions required by paragraph (i) of 

this AD are done before the compliance time 

specified in paragraph (g) of this AD: Before 

or concurrently with the accomplishment of 

the actions required by paragraph (i) of this 

AD, the modification required by paragraph 

(g) of this AD must be done. 

(n) Option to Requirements of Paragraphs (g) 

and (i) of This AD 

Accomplishment of all of the actions 

(including inspections and modification) 

specified in Boeing Service Bulletin 737–78– 

1079, Revision 2, dated June 7, 2010, within 

24 months after the effective date of this AD, 

is acceptable for compliance with the 

requirements of paragraphs (g) and (i) of this 

AD; except that this AD requires removing 

the affected compression pads and inspecting 

the underlying structures regardless whether 

a pad assembly is made of titanium or 

aluminum alloy. Accomplishment of all of 

the actions (including inspections and 

modification) specified in Boeing Service 

Bulletin 737–78–1079, Revision 2, dated June 

7, 2010, within 24 months after the effective 

date of this AD, is acceptable for compliance 

with the requirements of this AD provided 

applicable repairs are done before further 

flight, and provided the applicable actions 

specified in paragraphs (h)(1), (h)(2), and (l) 

of this AD have been done. This paragraph 

provides credit for the actions specified in 

Boeing Service Bulletin 737–78–1079, 

Revision 2, dated June 7, 2010, if those 

actions were done before the effective date of 

this AD using Boeing Service Bulletin 737– 

78–1079, dated August 6, 2007; or Revision 

1, dated December 17, 2007. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(p) Related Information 

For more information about this AD, 

contact Chris R. Parker, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6496; fax: 425–917– 

6590; email: chris.r.parker@faa.gov. 

(q) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Boeing Service Bulletin 737–78–1063, 

Revision 2, dated October 7, 1999. 

(ii) Boeing Service Bulletin 737–78–1069, 

Revision 4, dated June 16, 2005. 

(iii) Boeing Service Bulletin 737–78–1082, 

dated March 25, 2010. 

(iv) Boeing Service Bulletin 737–78–1088, 

dated May 12, 2010. 

(v) CFM CFM56–7B Service Bulletin 73– 

0135, dated March 30, 2007. 

(2) If you accomplish the optional actions 

specified by this AD, you must use the 

following service information to perform 

those actions, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference (IBR) of the following service 

information: 

(i) Boeing Service Bulletin 737–78–1079, 

Revision 2, dated June 7, 2010. 

(3) For Boeing 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; email 

me.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. For CFM service 

information identified in this AD, contact 

CFM International, Technical Publications 

Department, 1 Neumann Way, Cincinnati, 

Ohio 45215; phone: 513–552–2800; fax: 513– 

552–2816; Internet: http://www.cfm56.com. 

(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. 

(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 an NARA facility, 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 

22, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–8038 Filed 4–4–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0331; Directorate 

Identifier 2011–NM–119–AD; Amendment 

39–17008; AD 2012–07–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 all 

Airbus Model A340–500 and –600 series 

airplanes. This AD requires repetitive 

inspections of the forward and aft 

attachment fittings and of the swan neck 

for cracks, and replacing the attachment 

fittings and the swan neck with 

serviceable ones if necessary. This AD 

was prompted by reports of cracks on 

the forward attachment fittings of the 

left and right sides of the forward hinge 

of the nose landing gear (NLG) aft door. 

We are issuing this AD to detect and 

correct cracks of the forward attachment 

fittings and the swan neck, which could 

lead to the in-flight detachment of the 

NLG aft door and result in injury to 

persons on the ground or damage to the 

airplane. 

DATES: This AD becomes effective April 

20, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of the service information listed in the 

AD as of April 20, 2012. 

We must receive comments on this 

AD by May 21, 2012. 

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, 


rmajette on DSK2TPTVN1PROD with RULES
20516 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 

M–30, West Building Ground Floor, 

Room W12–140, 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 2011–0088, 

dated May 13, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

An operator has reported cracks on the aft 

hinge forward (FWD) fittings (hinge #5) of the 

NLG aft doors (Right Hand (RH) side or Left 

Hand (LH) side). The cracks extended by 

approximately 15 millimetres from the upper 

hole to the edge of the fittings. 

Investigation has revealed that these cracks 

have initiated due to fatigue loads and 

propagated under bending load. 

Cracks on the NLG aft door fittings, if not 

corrected, could lead to the inflight 

detachment of the door, possibly resulting in 

injury to persons on the ground or damage 

to the aeroplane. 

In order to maintain the structural integrity 

of the NLG aft door aft hinge attachment 

fittings, EASA issued EASA AD 2010–0028 

[which corresponds to FAA AD 2011–08–03, 

Amendment 39–16653 (71 FR 20496, April 

13, 2011)], which requires repetitive 

inspections at hinge #5. 

Additional investigations have shown that 

inspections are also necessary for the hinge 

#4. 

For the reasons described above, this 

[EASA] AD requires repetitive [detailed] 

inspections of the FWD and AFT attachment 

fittings and [high frequency eddy current 

inspections] of the swan neck at the forward 

hinge #4 and their replacement, as necessary. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–52–5017, including 

Appendices 1 and 2, dated February 17, 

2011. 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 

Although the MCAI or service 

information allows further flight after 

cracks are found, paragraph (g) of this 

AD requires that you replace both the 

forward and aft fittings before further 

flight if any crack is found. 

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–2012–0331; 

Directorate Identifier 2011–NM–119– 

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 that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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, 


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Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 20517 

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: 

2012–07–02 Airbus: Amendment 39–17008. 

Docket No. FAA–2012–0331; Directorate 

Identifier 2011–NM–119–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 20, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A340– 

541 and –642 airplanes, certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52: Doors. 

(e) Reason 

This AD was prompted by reports of cracks 

on the forward attachment fittings of the left 

and right sides of the forward hinge of the 

nose landing gear (NLG) aft door. We are 

issuing this AD to detect and correct cracks 

of the forward attachment fittings and the 

swan neck, which could lead to the in-flight 

detachment of the NLG aft door and result in 

injury to persons on the ground or damage 

to the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Inspections and Corrective 

Action of the Forward and Aft Attachment 

Fittings of the Forward Hinge (#4) of the 

NLG Aft Door 

Before the accumulation of 4,500 total 

flight cycles or within 50 flight cycles after 

the effective date of this AD, whichever 

occurs later: Do a detailed visual inspection 

for any cracking of the forward attachment 

fittings of the forward hinge (#4) of the NLG 

aft door of the left side and right side doors, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–52–5017, excluding 

Appendices 1 and 2, dated February 17, 

2011. 

(1) If no crack is found: Thereafter repeat 

the inspection required in paragraph (g) of 

this AD at intervals not to exceed 500 flight 

cycles. 

(2) If any crack is found during any 

inspection required in paragraph (g) of this 

AD: Before further flight, replace both the 

forward and aft fittings with serviceable 

fittings on the forward hinge (#4) of the 

affected NLG aft door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5017, 

excluding Appendices 1 and 2, dated 

February 17, 2011. 

(h) Action Requirement for Part 

Replacement of the Forward and Aft 

Attachment Fittings of the Forward Hinge 

(#4) of the NLG Aft Door 

If any forward and aft attachment fittings 

of the forward hinge (#4) of the NLG aft door 

have been replaced as required in paragraph 

(g)(2) of this AD: Before the accumulation of 

4,500 flight cycles on the forward fitting, do 

the inspection required in paragraph (g) of 

this AD. 

(i) Repetitive Inspections and Corrective 

Actions of the Swan Neck of the Forward 

Hinge (#4) of the NLG Aft Door 

Before the accumulation of 4,500 total 

flight cycles or within 50 flight cycles after 

the effective date of this AD, whichever 

occurs later: Perform a high frequency eddy 

current inspection for any cracking of the 

swan neck of the forward hinge (#4) of the 

NLG aft door of the left side and right side 

doors, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5017, 

excluding Appendices 1 and 2, dated 

February 17, 2011. 

(1) If no crack is found: Thereafter repeat 

the inspection required in paragraph (i) of 

this AD at intervals not to exceed 500 flight 

cycles. 

(2) If any crack is found during any 

inspection required in paragraphs (i) of this 

AD: Before further flight, replace the swan 

neck with a serviceable swan neck on the 

forward hinge (#4) of the affected NLG aft 

door, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–52–5017, 

excluding Appendices 1 and 2, dated 

February 17, 2011. 

(j) Action Requirement for Part Replacement 

of the Swan Neck of the Forward Hinge (#4) 

of the NLG Aft Door 

If any swan neck of the NLG aft door 

forward hinge (#4) is replaced as specified in 

paragraph (i)(2) of this AD: Before the 

accumulation of 4,500 flight cycles on the 

swan neck, repeat the inspection required in 

paragraph (i) of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to Attn: 

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. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding 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) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

not allowed. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2011–0088, dated May 13, 2011; 

and Airbus Mandatory Service Bulletin 

A340–52–5017, excluding Appendices 1 and 

2, dated February 17, 2011; for related 

information. 

(m) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(2) Airbus Mandatory Service Bulletin 

A340–52–5017, excluding Appendices 1 and 

2, dated February 17, 2011. 

(3) For Airbus service information 

identified in this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. 

(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. 

(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 an NARA facility, 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 March 

23, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7848 Filed 4–4–12; 8:45 am] 

BILLING CODE 4910–13–P 


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