Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37797 

Upon display of HYD:BACKUP PUMP HI 

TEMP (Abnormal procedure 3–250–15), set 

off the pump and if the backup pump is 

still rotating (green) in hydraulic synoptic, 

descend to a safe altitude or below 15,000 

ft 

Caution: These temporary amendments take 

precedence over the same procedures 

displayed through the Electronic Check 

List (ECL) in the aeroplane. 

Note 1 to paragraph (g) of this AD: When 

a statement identical to that in paragraph (g) 

of this AD has been included in the 

Limitations section and Abnormal 

Procedures section in the general revisions of 

the AFM, the general revisions may be 

inserted into the AFM, and the copy of this 

AD may be removed. 

(h) New Requirements of This AD: Test the 

PDCU and GCU Cards 

For airplanes identified in Dassault 

Mandatory Service Bulletin 7X–133, dated 

December 4, 2009: Within 9 months after the 

effective date of this AD, perform a test of the 

PDCU and GCU cards to detect faulty 

components, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–133, dated 

December 4, 2009. If any faulty components 

are found, before further flight, replace any 

affected PDCU or GCU card, in accordance 

with the Accomplishment Instructions of 

Dassault Mandatory Service Bulletin 7X–133, 

dated December 4, 2009. 

(i) Optional Method of Compliance 

For airplanes identified in Dassault 

Mandatory Service Bulletin 7X–133, dated 

December 4, 2009: Accomplishing the actions 

specified in paragraph (h) of this AD, within 

9 months after the effective date of this AD, 

in accordance with the service information 

specified in paragraphs (i)(1), (i)(2), and (i)(3) 

of this AD, is acceptable for compliance with 

the actions specified in paragraph (h) of this 

AD. 

(1) Goodrich Service Bulletin 80232190– 

24–01, dated August 13, 2009. 

(2) Goodrich Service Bulletin 80232191– 

24–01, dated August 13, 2009. 

(3) Goodrich Service Bulletin 80232192– 

24–01, dated August 13, 2009. 

(j) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0073, 

dated April 15, 2010, and the service 

bulletins specified in paragraphs (k)(1) 

through (k)(4) of this AD, for related 

information. 

(1) Dassault Mandatory Service Bulletin 

7X–133, dated December 4, 2009. 

(2) Goodrich Service Bulletin 80232190– 

24–01, dated August 13, 2009. 

(3) Goodrich Service Bulletin 80232191– 

24–01, dated August 13, 2009. 

(4) Goodrich Service Bulletin 80232192– 

24–01, dated August 13, 2009. 

(l) Material Incorporated by Reference 

(1) 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) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Dassault Mandatory Service Bulletin 

7X–133, dated December 4, 2009. 

(3) 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. 

(i) Goodrich Service Bulletin 80232190– 

24–01, dated August 13, 2009. 

(ii) Goodrich Service Bulletin 80232191– 

24–01, dated August 13, 2009. 

(iii) Goodrich Service Bulletin 80232192– 

24–01, dated August 13, 2009. 

(4) For Dassault service information 

identified in this AD, contact Dassault Falcon 

Jet, P.O. Box 2000, South Hackensack, New 

Jersey 07606; telephone 201–440–6700; 

Internet http://www.dassaultfalcon.com. For 

Goodrich service information identified in 

this AD, contact Goodrich Corporation, 

Power Systems, 1555 Corporate Woods 

Parkway, Uniontown, Ohio 44685–8799; 

telephone 330–487–2007; fax 330–487–1902; 

email twinsburg.techpubs@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(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 June 11, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15066 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0152; Directorate 

Identifier 2011–NM–059–AD; Amendment 

39–17092; AD 2012–12–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 series 

airplanes; Airbus Model A330–200 

Freighter series airplanes; Airbus Model 

A330–300 series airplanes; Airbus 

Model A340–200 series airplanes; and 

Airbus Model A340–300 series 

airplanes. This AD was prompted by 

reports of sheared fasteners located on 

the outside skin of the forward cargo 

door and cracks on the frame fork ends, 

as well as cracks of the aft cargo door 

frame 64A. This AD requires performing 

a detailed inspection of the outer skin 

rivets at the frame fork ends of the 

forward and aft cargo door for sheared, 

loose, and missing rivets; repairing the 

outer skin rivets, if necessary; and 

performing repetitive inspections. We 

are issuing this AD to detect and correct 

sheared, loose, or missing fasteners on 

the forward and aft cargo door frame, 

which could result in the loss of 

structural integrity of the forward and 

aft cargo door. 

DATES: This AD becomes effective July 

30, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 30, 2012. 

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, 


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37798 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

1200 New Jersey Avenue SE., 

Washington, DC. 

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 

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 February 23, 2012 (77 FR 

10691). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Two operators have reported cases of some 

sheared fasteners on the outside skin of the 

forward cargo door, detected during walk 

around checks. Further inspections revealed 

crack findings on the frame (FR) fork ends. 

In addition, during a scheduled 

maintenance check, the aft cargo door frame 

64A of an aeroplane has been found cracked 

for a length of more than 3 inches. Outer skin 

rivets were also found sheared. At time of 

findings the aeroplane had accumulated 

10564 flight cycles (FC), i.e. below the 12000 

FC threshold defined in DGAC [Direction 

Ge ́ne ́rale de l’Aviation Civile] France AD F– 

2001–124(B) and DGAC France AD F–2001– 

126(B) [which corresponds with FAA AD 

2001–16–01, Amendment 39–12369 (66 FR 

40874, August 6, 2001], which require a 

special detailed inspection of the aft cargo 

compartment door. 

In case of cracked or ruptured (forward or 

aft) cargo door frame, the loads will be 

transferred to the remaining structural 

elements. Such second load path is able to 

sustain the loads for a limited number of 

flight cycles only. Rupture of two vertical 

frames could result in the loss of the 

structural integrity of the forward or aft cargo 

door. 

For the above described reasons, this 

[EASA] AD requires repetitive detailed visual 

inspections of the aft and forward cargo 

doors outer skin for sheared, loose or missing 

rivets at all frame fork ends and the 

accomplishment of the applicable corrective 

actions [repair if necessary]. 

This [EASA] AD is considered to be an 

interim action, further actions might be 

required to revise/supersede the above 

mentioned DGAC France ADs. 

This [EASA] AD is revised in order to 

recognize that aeroplanes on which Airbus 

modification 44852 has been embodied in 

production are not affected by the repetitive 

inspection requirements of this [EASA] AD 

on the Aft Cargo Compartment Door. 

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 

received no comments on the NPRM (77 

FR 10691, February 23, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Clarification of the Repetitive 

Inspections 

For clarification purposes, we 

changed the interval for the repetitive 

inspections in paragraph (g) of this AD 

to the following: ‘‘* * * at intervals not 

to exceed 800 flight cycles.’’ The 

repetitive interval was stated incorrectly 

in the NPRM (77 FR 10691, February 23, 

2012) as 800 ‘‘total’’ flight cycles. 

Costs of Compliance 

We estimate that this AD will affect 

55 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $4,675, or $85 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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. 

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 (77 FR 10691, 

February 23, 2012), 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 adding 

the following new AD: 

2012–12–12 Airbus: Amendment 39–17092. 

Docket No. FAA–2012–0152; Directorate 

Identifier 2011–NM–059–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 


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Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37799 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

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 

sheared fasteners located on the outside skin 

of the forward cargo door and cracks on the 

frame fork ends, as well as cracks of the aft 

cargo door frame 64A. We are issuing this AD 

to detect and correct sheared, loose or 

missing fasteners on the forward and aft 

cargo door frame, which could result in the 

loss of structural integrity of the forward and 

aft cargo door. 

(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) Forward Cargo Compartment Door 

Before the accumulation of 6,000 total 

flight cycles since first flight of the airplane 

or within 400 flight cycles after the effective 

date of this AD, whichever occurs later: 

Perform a detailed inspection of the outer 

skin rivets at the frame fork ends between 

FR20B and FR25 of the forward cargo door 

for sheared, loose, and missing rivets, in 

accordance with the instructions of Airbus 

All Operators Telex (AOT) A330–52A3085, 

dated December 20, 2010 (for Model A330– 

200 and A330–300 series airplanes); or 

Airbus AOT A340–52A4092, dated December 

20, 2010 (for Model A340–200 and A340–300 

series airplanes). Thereafter repeat the 

inspection at intervals not to exceed 800 

flight cycles. 

(h) Aft Cargo Compartment Door 

For all airplanes, except those on which 

Airbus Modification 44854 or Modification 

44852 has been embodied in production, or 

Airbus Service Bulletin A330–52–3044 or 

Airbus Service Bulletin A340–52–4054 has 

been embodied in service: Before the 

accumulation of 4,000 total flight cycles 

since first flight of the airplane, or within 400 

flight cycles after the effective date of this 

AD, whichever occurs later, perform a 

detailed inspection of outer skin rivets at the 

frame fork ends between FR60 and FR64A of 

the aft cargo door for sheared, loose or 

missing rivets, in accordance with the 

instructions of Airbus AOT A330–52A3084, 

dated December 20, 2010 (for Model A330– 

200 and A330–300 series airplanes); or 

Airbus AOT A340–52A4091, dated December 

20, 2010 (for Model A340–200 and A340–300 

series airplanes). Thereafter repeat the 

inspection at intervals not to exceed 400 

flight cycles. 

(i) Corrective Action 

If any sheared, loose, or missing rivets are 

found during any inspection required by 

paragraph (g) or (h) of this AD: Before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

FAA; or European Aviation Safety Agency 

(EASA) (or its delegated agent). 

(j) 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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011– 

0007R1, dated February 14, 2011, and the 

service information specified in paragraphs 

(k)(1) through (k)(4) of this AD, for related 

information. 

(1) Airbus AOT A330–52A3085, dated 

December 20, 2010. 

(2) Airbus AOT A340–52A4092, dated 

December 20, 2010. 

(3) Airbus AOT A330–52A3084, dated 

December 20, 2010. 

(4) Airbus AOT A340–52A4091, dated 

December 20, 2010. 

(l) Material Incorporated by Reference 

(1) 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) You must use the following service 

information to do the actions required by this 

AD, as applicable, unless the AD specifies 

otherwise. 

(i) Airbus AOT A330–52A3085, dated 

December 20, 2010. The document number 

and date are identified only on the first page 

of this document. 

(ii) Airbus AOT A340–52A4092, dated 

December 20, 2010. The document number 

and date are identified only on the first page 

of this document. 

(iii) Airbus AOT A330–52A3084, dated 

December 20, 2010. The document number 

and date are identified only on the first page 

of this document. 

(iv) Airbus AOT A340–52A4091, dated 

December 20, 2010. The document number 

and date are identified only on the first page 

of this document. 

(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 June 7, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14730 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30847; Amdt. No. 3483] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 


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