This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

14679 

Vol. 77, No. 49 

Tuesday, March 13, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1087; Directorate 

Identifier 2011–NM–032–AD; Amendment 

39–16967; AD 2012–04–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding two 

existing airworthiness directives (AD). 

One existing AD is for Airbus Model 

A319, A320, and A321 series airplanes 

without Airbus modification 26017. 

That AD currently requires replacing the 

flight warning computers (FWCs). The 

other existing AD is for Airbus Model 

A320 and A321 series airplanes on 

which Airbus modification 24612 or 

Airbus Service Bulletin A320–31–1080 

has not been accomplished. That 

existing AD currently requires revising 

the limitations section of the airplane 

flight manual. This new AD requires 

replacing both FWC units with certain 

FWC units. This AD was prompted by 

in-service events of thrust lever 

mismanagement and a manufacturer 

analysis on the failure to follow 

procedure or heed existing cockpit cues. 

The analysis of the thrust lever 

management issue showed two 

categories of scenarios that could lead to 

thrust asymmetry during landing, with 

controllability and deceleration 

consequences. We are issuing this AD to 

prevent thrust asymmetry conditions 

which could result in loss of control of 

the airplane during landing. 

DATES: This AD becomes effective April 

17, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 17, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 24, 2002 (67 FR 35425, May 

20, 2002). 

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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; 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 October 19, 2011 (76 FR 

64854), and proposed to supersede AD 

97–22–13, Amendment 39–10185 (62 

FR 58891, October 31, 1997); and AD 

2002–10–06, Amendment 39–12752 (67 

FR 35425, May 20, 2002). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Following in-service experience, analyses 

of the failure to follow procedure or heed 

existing cockpit cues were conducted to 

assess the consequences of mismanagement 

of thrust levers during landing. 

The investigation results identified the 

need for improvements in the identification 

of throttle mis-positioning and so providing 

further opportunity for the flight crew to 

identify an incorrect thrust lever 

configuration and to correct this. For the 

A320 family of aeroplanes this being IDLE or 

REVERSE, which is necessary to enable 

ground spoiler (G/S) extension and autobrake (A/BRK) functions. In addition, the 

analysis of the thrust lever management issue 

shows two categories of scenarios that could 

lead to thrust asymmetry during landing with 

controllability and deceleration 

consequences: 

—One thrust lever kept in forward thrust 

when the other is put in IDLE or REVERSE. 

This has been seen in cases of dispatch 

with one thrust reverser inoperative; and 

—One thrust lever moved in forward position 

after landing, usually when bringing the 

thrust lever back from REVERSE to IDLE. 

These thrust asymmetry conditions, if not 

corrected, could result in loss of control of 

the aeroplane during landing. 

This [EASA] AD supersedes DGAC France 

AD 94–211–059(B) R2 and 96–079–079(B) 

[which corresponds to FAA AD 97–22–13 (62 

FR 58891, October 31, 1997], mandating 

Aircraft Flight Manual Temporary Revision 

reference 9.99.99/20 and the installation of 

FWC P/N 350E017248685 (H1D2) as 

terminating action for both ADs. 

This [EASA] AD retains the requirements 

of DGAC France AD 2000–320–147(B) [which 

corresponds to FAA AD 2002–10–06 (67 FR 

35425, May 20, 2002)], which is also 

superseded, which required the installation 

of FWC P/N 350E017271616 (H1E2). 

For the reasons described above, this 

[EASA] AD requires the replacement of both 

FWC units with minimum FWC P/N 

350E053020909 (H2F5) units, introducing 

‘‘Enhanced RETARD’’ logic. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM (76 FR 

64854, October 19, 2011). 

Explanation of Changes Made to This 

AD 

We have redesignated paragraph (g) 

and Note 1 of the NPRM (76 FR 64854, 

October 19, 2011) to paragraphs (g)(1) 

and (g)(2) in this AD, respectively. We 

have revised certain headings 

throughout this AD. We have also 

revised the wording in paragraphs (g)(2) 

and (j) of this AD; this change has not 

changed the intent of those paragraphs. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

64854, October 19, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 64854, 

October 19, 2011). 


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14680 Federal Register / Vol. 77, No. 49 / Tuesday, March 13, 2012 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD will affect 

about 729 products of U.S. registry. The 

actions that are required by AD 2002– 

10–06, Amendment 39–12752 (67 FR 

35425, May 20, 2002) and retained in 

this AD take about 7 work-hours per 

product, at an average labor rate of $85 

per work hour. Required parts would 

cost about $0 per product. Where the 

service information lists required parts 

costs that are covered under warranty, 

we have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, the estimated cost of the 

currently required actions is $595 per 

product. 

We estimate that it would take about 

4 work-hours per product to comply 

with the new basic requirements of this 

AD. The average labor rate is $85 per 

work-hour. Required parts would cost 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $247,860, or 

$340 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ’’significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (76 FR 64857, 

October 19, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing AD 97–22–13, Amendment 

39–10185 (62 FR 58891, October 31, 

1997); and AD 2002–10–06, 

Amendment 39–12752 (67 FR 35425, 

May 20, 2002); and adding the following 

new AD: 

2012–04–11 Airbus: Amendment 39–16967. 

Docket No. FAA–2011–1087; Directorate 

Identifier 2011–NM–032–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 17, 2012. 

(b) Affected ADs 

This AD supersedes AD 97–22–13, 

Amendment 39–10185 (62 FR 58891, October 

31, 1997); and AD 2002–10–06, Amendment 

39–12752 (67 FR 35425, May 20, 2002). 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all serial 

numbers; if equipped with a flight warning 

computer (FWC) with a part number (P/N) 

listed in table 1 of this AD. 

TABLE 1—LIST OF FWC PART

NUMBERS AFFECTED BY THIS AD 

FWC Part No. 

350E≤017238484 (H1D1) 

350E≤016187171 (C5) 

350E≤017248685 (H1D2) 

350E≤017251414 (H1E1) 

350E≤017271616 (H1E2) 

350E≤018291818 (H1E3CJ) 

350E≤018301919 (H1E3P) 

350E≤018312020 (H1E3Q) 

350E≤053020202 (H2E2) 

350E≤053020303 (H2E3) 

350E≤053020404 (H2E4) 

350E≤053020606 (H2F2) 

350E≤053020707 (H2F3) 

350E≤053021010 (H2F3P) 

350E≤053020808 (H2F4) 

(d) Subject 

Air Transport Association (ATA) of 

America Code 31: Indicating and Recording 

Systems. 

(e) Reason 

This AD was prompted by in-service 

events of thrust lever mismanagement and a 

manufacturer analysis on the failure to follow 

procedure or heed existing cockpit cues. The 

analysis of the thrust lever management issue 

showed two categories of scenarios that 

could lead to thrust asymmetry during 

landing, with controllability and deceleration 

consequences. We are issuing this AD to 

prevent thrust asymmetry conditions which 

could result in loss of control of the airplane 

during landing. 

(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) Restatement of Requirements of AD 2002– 

10–06, Amendment 39–12752 (67 FR 35425, 

May 20, 2002): Modification 

(1) For Model A319, A320, and A321 series 

airplanes without Airbus modification 26017: 

Within 18 months after June 24, 2002 (the 

effective date of AD 2002–10–06, 

Amendment 39–12752 (67 FR 35425, May 20, 

2002)), replace the flight warning computers 

(FWCs) in accordance with Airbus Service 

Bulletin A320–31–1106, Revision 04, dated 

December 21, 1999; or Airbus Mandatory 

Service Bulletin A320–31–1106, Revision 05, 

dated September 21, 2000. 

(2) This paragraph provides credit for 

replacement of the FWCs required by 


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Federal Register / Vol. 77, No. 49 / Tuesday, March 13, 2012 / Rules and Regulations 14681 

paragraph (g)(1) of this AD, if the 

replacement was done before June 24, 2002 

(the effective date of AD 2002–10–06, 

Amendment 39–12752 (67 FR 35425, May 20, 

2002)), using Airbus Service Bulletin A320– 

31–1106, dated January 3, 1997; Revision 01, 

dated April 16, 1997; Revision 02, dated 

January 20, 1998; or Revision 03, dated July 

9, 1999. 

(h) Restatement of Requirements of AD 

2002–10–06, Amendment 39–12752 (67 FR 

35425, May 20, 2002): Optional Method of 

Compliance 

Installation of a FWC standard in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

31–1141, Revision 04, dated February 14, 

2002, is an acceptable method of compliance 

with the replacement required by paragraph 

(g) of this AD. 

(i) New Requirements of This AD: Flight 

Warning Computer Replacement 

Within 48 months after the effective date 

of this AD: Replace both FWC units with 

FWC part number 350E053020909, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–31–1334, Revision 04, 

including Appendix 01, dated September 12, 

2011. 

(j) Credit for Previous Actions 

(1) For all airplanes, except for Model 

A319 series airplanes on which 

modifications 28238, 28162, and 28342 have 

been incorporated: This paragraph provides 

credit for replacing both FWCs, as required 

by paragraph (i) of this AD, if the 

replacements were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–31–1334, dated July 30, 2009; 

Revision 01, dated December 14, 2009; 

Revision 02, dated September 13, 2010; or 

Revision 03, dated March 15, 2011. 

(2) This paragraph provides credit for 

replacing both FWCs in lieu of the 

installation specified in paragraph (h) of this 

AD, if the replacements were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–31–1141, 

dated March 6, 2000; Revision 01, dated May 

25, 2000; Revision 02, dated January 22, 

2001; or Revision 03, dated June 12, 2001. 

(k) Parts Installation 

As of the effective date of this AD, and 

after accomplishing the actions in paragraph 

(i) of this AD, no person may install a FWC 

with a part number listed in table 1 of this 

AD on any airplane. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

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: 

Tim Dulin, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; telephone 

425–227–2141; 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. 

(m) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0001, dated January 10, 2011; 

Airbus Service Bulletin A320–31–1106, 

Revision 04, dated December 21, 1999; 

Airbus Mandatory Service Bulletin A320–31– 

1106, Revision 05, dated September 21, 2000; 

Airbus Service Bulletin A320–31–1141, 

Revision 04, dated February 14, 2002; and 

Airbus Mandatory Service Bulletin A320–31– 

1334, Revision 04, including Appendix 01, 

dated September 12, 2011; for related 

information. 

(n) 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 on the date 

specified. 

(2) The following service information was 

approved for IBR on April 17, 2012. 

(i) Airbus Mandatory Service Bulletin 

A320–31–1106, Revision 05, dated 

September 21, 2000. 

(ii) Airbus Service Bulletin A320–31–1141, 

Revision 04, dated February 14, 2002. 

(iii) Airbus Mandatory Service Bulletin 

A320–31–1334, Revision 04, including 

Appendix 01, dated September 12, 2011. 

(3) The following service information was 

approved for IBR on IBR June 24, 2002 (67 

FR 35425, May 20, 2002). 

(i) Airbus Service Bulletin A320–31–1106, 

Revision 04, dated December 21, 1999. 

(4) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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. 

(5) 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. 

(6) 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 January 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–5859 Filed 3–12–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0318; Directorate 

Identifier 2010–CE–033–AD; Amendment 

39–16966; AD 2012–04–10] 

RIN 2120–AA64 

Airworthiness Directives; Burl A. 

Rogers (Type Certificate Previously 

Held by William Brad Mitchell and 

Aeronca, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all Burl 

A. Rogers (type certificate previously 

held by William Brad Mitchell and 

Aeronca, Inc.) Models 15AC and S15AC 

airplanes. This AD was prompted by 

reports of intergranular exfoliation and 

corrosion of the upper and/or lower 

wing main spar cap angles found on the 

affected airplanes. This AD requires 

repetitive inspections of the upper and 

lower main wing spar cap angles for 

cracks and/or corrosion and installing 

inspection access panels. This AD also 

requires replacing the wing spar cap 

angles if moderate or severe corrosion is 

found and applying corrosion inhibitor. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD is effective April 17, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 17, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Burl’s 

Aircraft, LLC, P.O. Box 671487, 

Chugiak, Alaska 99567–1487; phone: 

(907) 688–3715; fax (907) 688–5031; 

email burl@biginalaska.com; Internet: 

http://www.burlac.com. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 


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