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

46929 

Vol. 77, No. 152 

Tuesday, August 7, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0802; Directorate 

Identifier 2012–NM–124–AD; Amendment 

39–17145; AD 2011–19–01 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) that 

applies to all Airbus Model A318, A319, 

A320, and A321 series airplanes. The 

existing AD currently requires revising 

the airplane flight manual (AFM) to 

include a procedure intended to address 

the unsafe condition, an inspection of 

the firewall connector for signs of arcing 

if an integrated drive generator (IDG) (or 

generator (GEN)) was shut down inflight automatically or using the AFM 

procedure, and corrective action if 

necessary; and provides an optional 

terminating action for certain AFM 

revision and inspections. This AD was 

prompted by the potential for an 

inadvertent error by flightcrew to use 

the IDG switch instead of the GEN 

switch when doing the AFM display 

unit failure procedure required by the 

existing AD. This AD retains the actions 

required by the existing AD and clarifies 

certain terminology. We are issuing this 

AD to prevent transient loss of certain 

systems, which could result in the 

reduced ability of the flightcrew to cope 

with adverse flight conditions. 

DATES: This AD becomes effective 

August 22, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 28, 2011 (76 FR 56279, 

September 13, 2011). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 13, 2004 (69 FR 

45243, July 29, 2004). 

We must receive comments on this 

AD by September 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, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 1, 2011, we issued AD 

2011–19–01, Amendment 39–16806 (76 

FR 56279, September 13, 2011). That 

AD required actions intended to address 

an unsafe condition on the products 

listed above. 

Since we issued AD 2011–19–01, 

Amendment 39–16806 (76 FR 56279, 

September 13, 2011), we have received 

information that there is potential for an 

inadvertent error by flightcrew to use 

the ‘‘IDG’’ (integrated drive generator) 

switch instead of the ‘‘GEN’’ 

(abbreviation for generator) switch when 

doing the AFM display unit failure 

procedure in this AD that requires 

turning off the integrated drive 

generator under certain conditions. We 

find that it is necessary to clarify our 

intent with the use of the acronym 

‘‘IDG’’ in relation to ‘‘GEN,’’ and to 

revise paragraphs (h), (i), and (k) of this 

AD to refer to ‘‘GEN.’’ 

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. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because transient loss of certain 

systems could result in the reduced 

ability of the flightcrew to cope with 

adverse flight conditions. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

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–2012–0802; 

Directorate Identifier 2012–NM–124– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 


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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); 

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, 

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 airworthiness directive (AD) 

2011–19–01, Amendment 39–16806 (76 

FR 56279, September 13, 2011), and 

adding the following new AD: 

2011–19–01 R1 Airbus: Amendment 39– 

17145; Docket No. FAA–2012–0802; 

Directorate Identifier 2012–NM–124–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective August 22, 2012. 

(b) Affected ADs 

This AD revises AD 2011–19–01, 

Amendment 39–16806 (76 FR 56279, 

September 13, 2011). 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, A318–112, A318–121, A318–122, A319– 

111, A319–112, A319–113, A319–114, A319– 

115, A319–131, A319–132, A319–133, A320– 

111, A320–211, A320–212, A320–214, A320– 

231, A320–232, A320–233, A321–111, A321– 

112, A321–131, A321–211, A321–212, A321– 

213, A321–231, and A321–232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 31: Instruments. 

(e) Reason 

This AD was prompted by reports of 

transient loss of certain systems and the 

potential for an inadvertent error by 

flightcrew to use the IDG switch instead of 

the GEN switch when doing a certain 

airplane flight manual (AFM) display unit 

failure procedure. We are issuing this AD to 

prevent transient loss of certain systems, 

which could result in the reduced ability of 

the flightcrew to cope with adverse flight 

conditions. 

(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) Retained Revision of Airplane Flight 

Manual (AFM) 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–19–01, 

Amendment 39–16806 (76 FR 56279, 

September 13, 2011). For Airbus Model 

A319–131, –132, and –133, A320–231, –232, 

and –233, and A321–131 and –231 series 

airplanes, except those airplanes on which 

Airbus Modification 32943 has been 

incorporated in production: Within 10 days 

after August 13, 2004 (the effective date of 

AD 2004–15–14, Amendment 39–13748 (69 

FR 45243, July 29, 2004)), revise the 

Limitations section of the Airbus A318/319/ 

320/321 AFM to include the information in 

Temporary Revision (TR) 4.02.00/20, dated 

May 3, 2004. This may be done by inserting 

a copy of this TR into the AFM. When this 

TR has been included in general revisions of 

the AFM, those general revisions may be 

inserted into this AFM, provided the relevant 

information in the general revisions is 

identical to that in this TR. Accomplishing 

the actions required by paragraph (j) of this 

AD terminates the requirements of this 

paragraph. 

(h) Retained Post-Integrated Drive Generator 

Shutdown Inspection 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–19–01, 

Amendment 39–16806 (76 FR 56279, 

September 13, 2011), with replacement of the 

term ‘‘IDG’’ with ‘‘GEN.’’ For Airbus Model 

A319–131, –132, and –133, A320–231, –232, 

and –233, and A321–131 and –231 series 

airplanes, except those airplanes on which 

Airbus Modification 32943 has been 

incorporated in production: If a GEN is shut 

down by the flightcrew in accordance with 

the TR procedures specified in paragraph (g) 

of this AD, or if a GEN is shut down 

automatically before September 28, 2011 (the 

effective date of AD 2011–19–01), do the 

actions specified in paragraph (h)(1) or (h)(2) 

of this AD. If a GEN is shut down 

automatically on or after September 28, 2011, 

do the actions specified in paragraph (k) of 

this AD. 

(1) Before further flight, inspect the 

firewall connector of the affected GEN to 

detect signs of arcing, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA. If any sign of 

arcing is detected: Before further flight, either 

repair the connector or replace the connector 

with a new connector, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116. 

(2) Operate the airplane with the affected 

GEN inoperative in accordance with the 

provisions and compliance periods specified 

in the FAA-approved Master Minimum 

Equipment List or in accordance with a 

method approved by the Manager, 

International Branch, ANM–116. Before 

further use of the affected GEN, do the 

actions specified in paragraph (h)(1) of this 

AD. As September 28, 2011 (the effective 

date of AD 2011–19–01, Amendment 39– 

16806 (76 FR 56279, September 13, 2011), 

operate the airplane in accordance with a 

method approved by the Manager, 

International Branch, ANM–116. 


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Federal Register / Vol. 77, No. 152 / Tuesday, August 7, 2012 / Rules and Regulations 46931 

Note 1 to paragraph (h) of this AD: 

Guidance on provisions and compliance 

periods for operating the airplane with an 

inoperative, affected GEN can be found in the 

FAA-approved Master Minimum Equipment 

List. 

(i) Retained Terminating Action for 

Paragraphs (g) and (h) of This AD if Done 

Before September 28, 2011 (the Effective 

Date of AD 2011–19–01, Amendment 39– 

16806 (76 FR 56279, September 13, 2011)) 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–19–01, Amendment 

39–16806 (76 FR 56279, September 13, 2011), 

with replacement of the term ‘‘IDG’’ with 

‘‘GEN.’’ For Airbus Model A319–131, –132, 

and –133, A320–231, –232, and –233, and 

A321–131 and –231 series airplanes, except 

those airplanes on which Airbus 

Modification 32943 has been incorporated in 

production: Replacement of the GEN 

harnesses and connectors on both engines in 

accordance with Airbus Service Bulletin 

A320–71–1030, dated February 27, 2003, 

before September 28, 2011 (the effective date 

of AD 2011–19–01), terminates the 

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

AD. 

Note 2 to paragraph (i) of this AD: Airbus 

Service Bulletin A320–71–1030, dated 

February 27, 2003, refers to International 

Aero Engines Information Bulletin V2500– 

NAC–70–0736, dated January 28, 2003, as an 

additional source of guidance for the 

harness/connector replacement specified in 

paragraph (i) of this AD. 

(j) Retained AFM Revision 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–19–01, Amendment 

39–16806 (76 FR 56279, September 13, 2011). 

For all airplanes: Within 10 days after 

September 28, 2011 (the effective date of AD 

2011–19–01), revise the applicable section of 

the Airbus A318/319/320/321 AFM to 

include the information in Figure 1 to 

paragraph (j) of this AD or the information in 

Airbus TR TR112, Issue 1.1, dated November 

29, 2010, to the Airbus A318/319/320/321 

AFM. This may be done by inserting a copy 

of this AD or Airbus TR TR112, Issue 1.1, 

dated November 29, 2010, in the AFM. 

Accomplishing the actions required by this 

paragraph terminates the requirements of 

paragraph (g) of this AD. 

Note 3 to paragraph (j) of this AD: When 

the information in Figure 1 to paragraph (j) 

of this AD or Airbus TR TR112, Issue 1.1, 

dated November 29, 2010, to the Airbus 

A318/319/320/321 AFM, has been included 

in the applicable section of the general 

revisions of the AFM, the general revisions 

may be inserted into the AFM, and the copy 

of this AD may be removed from the AFM, 

provided the relevant information in the 

general revisions is identical to that in Figure 

1 to paragraph (j) of this AD or Airbus TR 

TR112, Issue 1.1, dated November 29, 2010. 

DISPLAY UNIT FAILURE 

D Affected DU blank or display distorted: 

Turn off affected DU as required. 

• If ECAM DUs affected: Use ECAM/ND SEL 

• If EFIS DUs affected: Use PFD/ND XFR. 

D Diagonal line or ‘‘INVALID DATA’’ on affected DU: 

Attempt to recover affected DU by using associated DMC switching. 

• If unsuccessful: Turn off then on affected DU. 

D Inversion of EWD and SD displays: Turn off then on ECAM upper display. 

D Affected DU(s) or MCDU flashes intermittently: 

D If Captain PFD or ND, both ECAM DUs or upper ECAM DU, or MCDU 1 is (are) affected: Turn off GEN 1. 

D If DU(s) stop(s) flashing: Keen GEN 1 off for the rest of the flight. Use the sideslip indication to verify if the rudder trim needs 

to be reset. If necessary, reset the rudder trim. Note: Intermittent Electrical Power Supply Interruptions may cause offset in the 

rudder trim. Select AP and/or autothrust as required. APU may be started (Refer to NORM-49 Auxiliary Power Unit (APU) and 

APU generator may be used (if available). 

D If DU(s) do(es) not stop flashing: Restore GEN 1. 

D If First Officer PFD or ND, lower ECAM DU, or MCDU 2 is (are) affected: Turn off GEN 2. 

D If DU(s) stop(s) flashing: Keep GEN 2 off for the rest of the flight. Use the sideslip indication to verify if the rudder trim needs 

to be reset. If necessary, reset the rudder trim. Note: Intermittent Electrical Power Supply Interruptions may cause offset in the 

rudder trim. Select AP and/or autothrust as required. APU may be started (Refer to NORM-49 Auxiliary Power Unit (APU)) and 

APU generator may be used (if available). 

D If DU(s) do(es) not stop flashing: Restore GEN 2. 

Figure 1 to Paragraph (j) 

(k) Retained Post-Integrated Drive Generator 

Shutdown Inspection 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–19–01, 

Amendment 39–16806 (76 FR 56279, 

September 13, 2011), with replacement of the 

term ‘‘IDG’’ with ‘‘GEN.’’ For all airplanes: If 

a GEN is shut down by the flightcrew in 

accordance with the TR procedures specified 

in paragraph (j) of this AD, or if a GEN is shut 

down automatically on or after September 28, 

2011 (the effective date of AD 2011–19–01), 

do the actions specified in paragraph (k)(1) 

or (k)(2) of this AD. 

(1) Before further flight, inspect the 

firewall connector of the affected GEN to 

detect signs of arcing, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA. If any sign of 

arcing is detected: Before further flight, either 

repair the connector or replace the connector 

with a new connector, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116. 

(2) Operate the airplane with the affected 

GEN inoperative in accordance with a 

method approved by the Manager, 

International Branch, ANM–116. Before 

further use of the affected GEN, do the 

actions specified in paragraph (k)(1) of this 

AD. 

Note 4 to paragraph (k) of this AD: 

Guidance on provisions and compliance 

periods for operating the airplane with an 

inoperative, affected GEN can be found in the 

FAA-approved Master Minimum Equipment 

List. 

(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, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149 Information may be emailed to: 9-ANM116-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. 

AMOCs approved previously for AD 2004– 

15–14, Amendment 39–13748 (69 FR 45243, 

July 29, 2004), are acceptable for the 

corresponding provisions of this AD. AMOCs 

approved previously in accordance with AD 

2011–19–01, Amendment 39–16806 (76 FR 

56279, September 13, 2011), are not 

approved as AMOCs with 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 


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to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0142, dated July 25, 2011, and the 

service information identified in paragraphs 

(m)(1), (m)(2), and (m)(3) of this AD for 

related information. 

(1) Airbus TR 4.02.00/20, dated May 3, 

2004, to the Airbus A318/319/320/321 AFM. 

(2) Airbus TR TR112, Issue 1.1, dated 

November 29, 2010, to the Airbus A318/319/ 

320/321 AFM. 

(3) Airbus Service Bulletin A320–71–1030, 

dated February 27, 2003. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 28, 2011 (76 

FR 56279, September 13, 2011). 

(i) Airbus Temporary Revision TR112, 

Issue 1.1, dated November 29, 2010, to the 

Airbus A318/319/320/321 (AFM) Airplane 

Flight Manual. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 13, 2004 (69 FR 

45243, July 29, 2004). 

(i) Airbus Service Bulletin A320–71–1030, 

dated February 27, 2003. 

(ii) Airbus Temporary Revision 4.02.00/20, 

dated May 3, 2004, to the Airbus A318/319/ 

320/321 AFM (Airplane Flight Manual). 

(5) For Airbus 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(6) You may review copies of the 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. 

(7) 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 July 23, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18625 Filed 8–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1322; Directorate 

Identifier 2011–NM–211–AD; Amendment 

39–17141; AD 2012–15–12] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 767 airplanes. 

This AD was prompted by reports of 

cracks of the underwing longeron 

fittings in the wing center section. This 

AD requires repetitive inspections of the 

underwing longeron fitting for cracking, 

and related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct such cracking, 

which could result in loss of the 

primary load path between the fuselage 

and the wing box, and consequent 

catastrophic damage to the wing box 

and failure of the wing. 

DATES: This AD is effective September 

11, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 11, 2012. 

ADDRESSES: For 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; phone: 206–544–5000, extension 

1; fax: 206–766–5680; Internet: https:// 

www.myboeingfleet.com. You may 

review copies of the referenced 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

Berhane.Alazar@faa.gov. 

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 published in the Federal 

Register on December 19, 2011 (76 FR 

78574). That NPRM proposed to require 

repetitive high frequency eddy current 

(HFEC) inspections of the underwing 

longeron fitting for cracking, and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 78574, 

December 19, 2011), and the FAA’s 

response to each comment. 

Request To Use Revised Service 

Information 

Boeing, UPS, and United Airlines 

(United) requested that the NPRM (76 

FR 78574, December 19, 2011) use the 

revised service information, which is 

Boeing Alert Service Bulletin 767– 

57A0126, Revision 2, dated March 12, 

2012. (The NPRM referred to Boeing 

Alert Service Bulletin 767–57A0126, 

dated August 12, 2011, as revised by 

Boeing Service Bulletin 767–57A0126, 

Revision 1, dated November 9, 2011, as 

the appropriate source of service 

information for accomplishing the 

proposed requirements.) Boeing stated 

that the correction of the airplane 

variable effectivity table does not 

change the intent of the NPRM, because 

applicability paragraph (c) of the NPRM 

states that ‘‘This AD applies to all The 

Boeing Company Model 767–200, –300, 

–300F and –400ER series airplanes; 

certified in any category.’’ Boeing also 

stated that including Boeing Alert 

Service Bulletin 767–57A0126, Revision 

2, dated March 12, 2012, in the AD 

might prevent confusion for operators of 

these airplanes. 

We agree with this request because 

Boeing Alert Service Bulletin 767– 

57A0126, Revision 2, dated March 12, 

2012, clarifies inspection areas and 


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