Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 15261 

approval of a transaction, activity, or 

item. 

§ 1211.4 Non-Objection Letters. 

(a) Authority. The Deputy Directors 

for Enterprise Regulation and for 

Federal Home Loan Bank Regulation, or 

their designees, may, in their discretion, 

issue to an Enterprise or to a Bank or the 

Office of Finance, respectively, a NonObjection Letter stating that FHFA does 

not object to a proposed transaction or 

activity for supervisory, regulatory, or 

policy reasons. The Director reserves the 

right to modify, rescind, or supersede a 

Non-Objection Letter, with such action 

being effective only on a prospective 

basis. 

(b) Requests. A regulated entity or the 

Office of Finance may request a NonObjection Letter in accordance with 

§ 1211.6. 

§ 1211.5 Regulatory Interpretations. 

(a) Authority. The General Counsel 

may, in his or her discretion, issue a 

Regulatory Interpretation to a regulated 

entity or the Office of Finance, 

providing guidance with respect to the 

application of any applicable statute, 

rule, regulation, or order to a proposed 

transaction or activity. The Director 

reserves the right to modify, rescind, or 

supersede a Regulatory Interpretation, 

with such action being effective only on 

a prospective basis. 

(b) Requests. A regulated entity or the 

Office of Finance may request a 

Regulatory Interpretation in accordance 

with § 1211.6. 

§ 1211.6 Submission requirements. 

Applications for a Waiver or Approval 

and requests for a Non-Objection Letter 

or Regulatory Interpretation shall 

comply with the requirements of this 

section and shall pertain to regulatory 

matters relating to the Banks or 

Enterprises, and not to conservatorship 

matters. 

(a) Filing. Each application or request 

shall be in writing. A Bank or the Office 

of Finance shall submit its filing to the 

Deputy Director for the Division of 

Federal Home Loan Bank Regulation, 

and an Enterprise shall submit its filing 

to the Deputy Director for Enterprise 

Regulation. Applications for regulatory 

interpretations shall be submitted also 

to the General Counsel. 

(b) Authorization. An application for 

a Waiver or Approval and a request for 

a Non-Objection Letter or Regulatory 

Interpretation shall be signed by the 

president of the regulated entity or by 

the chairperson of the board of directors 

of the Office of Finance, as appropriate. 

Applications for Waiver or Approval 

also shall be accompanied by a 

resolution of the board of directors 

concurring in the substance and 

authorizing the filing of the application. 

(c) Information requirements. Each 

application or request shall contain: 

(1) The name of the requester, and the 

name, title, business address, telephone 

number, and business electronic mail 

address, if any, of the official filing the 

application or request on its behalf; 

(2) The name, business address, 

telephone number, and business 

electronic mail address, if any, of a 

contact person from whom FHFA staff 

may seek additional information if 

necessary; 

(3) The section numbers of the 

particular provisions of the applicable 

statutes or rules, regulations, policies, or 

orders to which the application or 

request relates; 

(4) Identification of the determination 

or relief requested, including any 

alternative relief requested if the 

primary relief is denied, and a clear 

statement of why such relief is needed; 

(5) A statement of the particular facts 

and circumstances giving rise to the 

application or request and identifying 

all relevant legal and factual issues; 

(6) References to all other relevant 

authorities, including the Authorizing 

Statutes, Safety and Soundness Act, 

FHFA rules, regulations, policies, and 

orders, judicial decisions, 

administrative decisions, relevant 

statutory interpretations, and policy 

statements; 

(7) References to any Waivers, NonObjection Letters, Approvals, or 

Regulatory Interpretations issued in the 

past in response to circumstances 

similar to those surrounding the request 

or application; 

(8) For any application or request 

involving interpretation of the 

Authorizing Statutes, Safety and 

Soundness Act, or FHFA regulations, a 

reasoned opinion of counsel supporting 

the relief or interpretation sought and 

distinguishing any adverse authority; 

(9) Any other non-duplicative, 

relevant supporting documentation; and 

(10) A certification by a person with 

knowledge of the facts that the 

representations made in the application 

or request are accurate and complete. 

The following form of certification is 

sufficient for this purpose: ‘‘I hereby 

certify that the statements contained in 

the submission are true and complete to 

the best of my knowledge. [Name and 

Title].’’ 

(d) Exceptions. In any given matter or 

class of matters, the Director, the Deputy 

Director for Federal Home Loan Bank 

Regulation, the Deputy Director for 

Enterprise Regulation, or the General 

Counsel, as appropriate, may accept an 

application or request that does not 

comply with the requirements of this 

section, for supervisory reasons or 

administrative efficiency. 

(e) Withdrawal. Once filed, an 

application or request may be 

withdrawn only upon written request, 

and only if FHFA has not yet acted on 

the application or request. 

Dated: March 13, 2014. 

Melvin L. Watt, 

Director, Federal Housing Finance Agency. 

[FR Doc. 2014–06033 Filed 3–18–14; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23706; Directorate 

Identifier 2006–NE–03–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2006–15– 

08, which applies to all Honeywell 

International Inc. TPE331–1, –2, –2UA, 

–3U, –3UW, –5, –5A, –5AB, –5B, –6, 

–6A, –10, –10AV, –10GP, –10GT, –10P, 

–10R, –10T, –10U, –10UA, –10UF, 

–10UG, –10UGR, –10UR, –11U, –12JR, 

–12UA, –12UAR, and –12UHR 

turboprop engines with certain part 

numbers (P/Ns) of Woodward fuel 

control unit (FCU) assemblies, installed. 

AD 2006–15–08 currently requires 

initial and repetitive dimensional 

inspections of the fuel control drive 

spline for wear, and replacement of the 

FCU and fuel pump. Since we issued 

AD 2006–15–08, we determined that 

additional FCU assembly P/Ns are 

affected, the compliance deadline and 

assembly replacement after removal for 

cause or overhaul are no longer 

required, and that cautionary engine 

operating information must be observed. 

This proposed AD was prompted by 

reports of loss of the fuel control drive, 

leading to engine overspeed, overtorque, 

overtemperature, uncontained rotor 

failure, and asymmetric thrust in multiengine airplanes. This proposed AD 

would require initial and repetitive 

dimensional inspections of the affected 

fuel control drive splines, and insertion 

of certain airplane operating procedures 

into the applicable flight manuals. We 


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are proposing this AD to prevent failure 

of the fuel control drive that could 

result in damage to the engine and 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 19, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Honeywell 

International Inc., 111 S 34th Street, 

Phoenix, AZ 85034–2802; phone: 800– 

601–3099; Internet: https://

myaerospace.honeywell.com/wps/

portal/!ut/. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2006– 

23706; 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 proposed AD, the 

regulatory evaluation, any comments 

received and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: joseph.costa@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–23706; Directorate Identifier 

2006–NE–03–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On July 14, 2006, we issued AD 2006– 

15–08, Amendment 39–14688 (71 FR 

41121, July 20, 2006), for all Honeywell 

International Inc. TPE331 series 

turboprop engines with certain P/Ns of 

Woodward FCU assemblies installed. 

AD 2006–15–08 requires initial and 

repetitive dimensional inspections of 

the fuel control drive spline for wear 

that might cause replacement of the 

FCU and/or fuel pump assemblies. AD 

2006–15–08 also requires the 

replacement of the FCU assembly when 

the FCU is removed for cause or 

overhaul, but not later than December 

31, 2012. AD 2006–15–08 was prompted 

by fuel control drive failures that 

resulted in a rapid, uncommanded, 

uncontrolled increase in fuel flow and 

overspeed of the engine during ground 

start. We issued AD 2006–15–08 to 

prevent failure of the fuel control drive, 

destructive overspeed that could result 

in uncontained rotor failure and damage 

to the airplane. 

Actions Since AD 2006–15–08 Was 

Issued 

Since we issued AD 2006–15–08, 

Amendment 39–14688 (71 FR 41121, 

July 20, 2006), we determined that 

additional FCU assembly P/Ns are 

affected, certain repetitive fuel control 

drive inspections are necessary, and that 

additional flight crew emergency 

procedures and warnings are required. 

The warnings are required to inform 

flight crew of the probable engine 

response(s) following a loss of drive 

between the engine driven fuel pump 

and fuel control governor system. These 

engine responses are dependent on the 

phase of operation (ground engine start, 

ground or flight operations). 

Also since we issued AD 2006–15–08, 

Amendment 39–14688 (71 FR 41121, 

July 20, 2006), we reviewed the inservice trends and engine in-flight 

shutdowns (IFSDs) caused by the 

modified FCU and determined that the 

IFSD rate had not improved and the 

installation of the modified FCU 

assembly was not required. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

continued dimensional spline 

inspections required by AD 2006–15– 

08, add new P/Ns of affected FCU 

assemblies that require dimensional 

spline inspections. This proposed AD 

would require insertion of 

uncommanded engine overspeed 

procedures into the Airplane Flight 

Manual, Pilot Operating Handbook, and 

or Manufacturer’s Operating Manual. 

This proposed AD would retain some 

but not all requirements of AD 2006– 

15–08, (71 FR 41121, July 20, 2006), but 

would no longer require the installation 

of a modified FCU. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 2,250 engines installed on 

airplanes of U.S. registry. We estimate 

that it would take 8 hours per engine to 

perform an FCU inspection, and three 

inspections will be required over the life 

of the product. The average labor rate is 

$85 per hour. Due to the more frequent 

inspections proposed by this AD, we 

estimate 10% of affected engines would 

require FCU assembly stub shaft 

replacement, fuel pump or fuel control 

repair. We also estimate that repairs 

should not exceed $10,000 per engine. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $6,307,044. 

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 


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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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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 to the extent that it justifies 

making a regulatory distinction, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. Amend § 39.13 by removing 

airworthiness directive (AD) 2006–15– 

08, Amendment 39–14688 (71 FR 

41121, July 20, 2006), and adding the 

following new AD: 

Honeywell International Inc.: Docket No. 

FAA–2006–23706; Directorate Identifier 

2006–NE–03–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 19, 2014. 

(b) Affected ADs 

This AD supersedes AD 2006–15–08, 

Amendment 39–14688 (71 FR 41121, July 20, 

2006). 

(c) Applicability 

This AD applies to all Honeywell 

International Inc. TPE331–1, –2, –2UA, –3U, 

–3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, 

–10AV, –10GP, –10GT, –10P, –10R, –10T, 

–10U, –10UA, –10UF, –10UG, –10UGR, 

–10UR, –11U, –12JR, –12UA, –12UAR, and 

–12UHR turboprop engines with the part 

numbers (P/Ns) of Woodward fuel control 

unit (FCU) assemblies listed in Table 1 to 

paragraph (c) of this AD, installed. 

TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS

Group # Engine FCU Assembly P/Ns 

1 ......................... TPE331–1, –2, and –2UA ....................... P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, 

–33, –34, and –35. 

2* ....................... TPE331–1, –2, and –2UA ....................... P/N 869199–9, –10, –11, –12, –14, –16, –17, and –18. 

3 ......................... TPE331–3U, –3UW, –5, –5A, –5AB, 

–5B, –6, –6A, –l0AV, –10GP, –10GT, 

–l0P, and –l0T.

P/N 893561–7, –8, –9, –10, –11, –14, –15, –16, –20, –26, –27, and –29; or P/N 

897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. 

4* ....................... TPE331–3U, –3UW, –5, –5A, –5AB, 

–5B, –6, –6A, –l0AV, –10GP, –10GT, 

–l0P, and –l0T.

P/N 893561–4, –5, –12, and –13 or P/N 897770–5, –8, and –13. 

5 ......................... TPE331–10, –l0R, –10U, –10UA, 

–10UF, –10UG, –10UGR, –10UR, 

–11U, –12JR, –12UA, –12UAR, and 

–12UHR.

P/N 897375–2, –3, –4, –5, –8, –9, –10, –11, –12, –13, –14, –15, –16, –17, –19, 

–21, –24, –25, –26, and –27; or P/N 897780–1, –2, –3, –4, –5, –6, –7, –8, –9, 

–10, –11, –14, –15, –16, –17, –18, –19, –20, –21, –22, –23, –24, –25, –26, 

–27, –30, –32, –34, –36, –37, and –38; or P/N 893561–17, –18, and –19. 

* New/added FCU assembly P/Ns 

(d) Unsafe Condition 

This AD was prompted by reports of loss 

of the fuel control drive, leading to engine 

overspeed and engine failure. We are issuing 

this AD to prevent damage to the engine, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Inspection of Engines with FCU Assembly 

P/Ns in Groups 2 and 4 

For FCU assembly P/Ns in Groups 2 and 

4 listed in Table 1 to paragraph (c) of this AD, 

at the next scheduled inspection of the fuel 

control drive, or within 500 hours-in-service 

(HIS) after the effective date of this AD, 

whichever occurs first: 

(i) Inspect the fuel control drive spline for 

wear. 

(ii) Thereafter, re-inspect the fuel control 

drive within 1,000 HIS since-last-inspection 

(SLI) of the fuel control drive. 

(2) Inspection of Engines with FCU Assembly 

P/Ns in Groups 1, 3, and 5 

(i) For FCU assembly P/Ns in Groups 1, 3, 

or 5 listed in Table 1 to paragraph (c) of this 

AD: 

(A) If on the effective date of this AD the 

FCU assembly has 950 or more HIS SLI, 

inspect the fuel control drive spline for wear 

within 50 HIS from the effective date of this 

AD. 

(B) If on the effective date of this AD the 

FCU assembly has fewer than 950 HIS SLI, 

inspect the fuel control drive spline for wear 

before reaching 1,000 HIS. 

(ii) Thereafter, re-inspect the fuel control 

drive spline for wear within every 1,000 HIS 

SLI. 

(3) Airplane Operating Procedures 

Within 60 days after the effective date of 

this AD, insert the information in Figure 1 to 

paragraph (e) of this AD, into the Emergency 

Procedures Section of the Airplane Flight 

Manual (AFM), Pilot Operating Handbook 

(POH), and the Manufacturer’s Operating 

Manual (MOM). 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(f) Optional Terminating Action 

Replacing the affected FCU assembly with 

an FCU assembly P/N not listed in this AD 

is terminating action for the initial and 

repetitive inspections required by this AD, 

and for inserting the information in Figure 1 

to paragraph (e) of this AD into the AFM, 

POH, and MOM. 

(g) Definitions 

For the purposes of this AD: 

(1) The ‘‘fuel control drive’’ is a series of 

mating splines located between the fuel 

pump and fuel control governor. 

(2) The fuel control drive consists of four 

drive splines: the fuel pump internal spline, 

the fuel control external ‘‘quill shaft’’ spline, 

and the stub shaft internal and external 

splines. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(2) Honeywell International Inc., AFM, 

POH, and MOM, which are not incorporated 

by reference in this AD, can be obtained from 

Honeywell International Inc., using the 

contact information in paragraph (i)(4) of this 

AD. 

(3) Information pertaining to operating 

recommendations for affected engines after a 

fuel control drive failure is contained in 

Honeywell International Inc., Operating 

Information Letter (OIL) OI331–12R6, dated 


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May 26, 2009, for multi-engine airplanes; and 

in OIL OI331–18R4, dated May 26, 2009, for 

single-engine airplanes. Information on fuel 

control drive spline inspection can be found 

in Section 72–00–00 of the applicable 

TPE331 maintenance manuals. These 

Honeywell International Inc., OILs and the 

TPE331 maintenance manuals, which are not 

incorporated by reference in this AD, can be 

obtained from Honeywell International Inc., 

using the contact information in paragraph 

(i)(4) of this AD. 

(4) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; Internet: https://

myaerospace.honeywell.com/wps/portal/!ut; 

phone: 800–601–3099. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

March 10, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–06029 Filed 3–18–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0143; Directorate 

Identifier 2012–NM–113–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A300 B4–603, B4–620, 

B4–622, B4–605R, B4–622R; F4–605R, 

F4–622R and C4–605R variant F 

airplanes. This proposed AD was 

prompted by reports of cracks in the 

frame base fittings connecting the frame 

lower positions to the center wing box. 

This proposed AD would require 

repetitive detailed inspections of the 

lower frame fittings, related 

investigative actions, and corrective 

actions if necessary. We are proposing 

this AD to detect and correct cracking 

on the lower frame fittings, which could 

reduce the structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 5, 2014. 

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 

W12–140, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0143; 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 proposed 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0143; Directorate Identifier 

2012–NM–113–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

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 2012–0103, 

dated June 11, 2012 (corrected June 19, 

2012) (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During maintenance checks, cracks were 

discovered by A300 and A300–600 operators 

in the frame [base] feet fittings, connecting 

the frame lower positions to the centre wing 

box. 

These occurrences were followed by a 

dedicated sampling inspection programme 

carried out by Airbus. During this sampling 

programme, 22 A300–600 aeroplanes were 

found with cracks on the lower fittings of 

frame 44 to frame 46 left hand (LH) and right 

hand (RH) side. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the fuselage of all aeroplanes operated up 

to the extended service goal (ESG). 

For the reasons described above, this 

[EASA] AD requires repetitive detailed visual 

inspections [for discrepancies (cracking)] of 

the lower frame fittings between frame 41 

and frame 46 and, depending on findings, 

accomplishment of a repair. 

This [EASA] AD has been republished to 

correct Note 2 in Appendix 1. 

Related investigative actions include 

doing a rotating probe inspection for 

cracking of the crack stop hole. 

Corrective actions include repairing or 

replacing cracking and cracked base 

fittings. You may examine the MCAI in 

the AD docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0143. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A300–53–6111, Revision 05, 

including Appendix 01, dated January 

28, 2013. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 


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