Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66653 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 5 years after the effective date 

of this AD, replace the wing tank main pump 

pressure switches having P/N HTE69000–1 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–28–3111, Revision 02, dated 

March 24, 2010. 

(h) Actions accomplished before the 

effective date of this AD according to Airbus 

Mandatory Service Bulletin A330–28–3111, 

dated August 12, 2009; or Revision 01, dated 

December 4, 2009; are considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences 

Other FAA AD Provisions 

(i) 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. 

Send information 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. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0018, 

dated February 4, 2010; and Airbus 

Mandatory Service Bulletin A330–28–3111, 

Revision 02, dated March 24, 2010; for 

related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A330–28–3111, Revision 02, 

dated March 24, 2010, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For 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; e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) 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. 

(4) 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 NARA, 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 October 

13, 2010. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–26553 Filed 10–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0645; Directorate 

Identifier 2009–NM–200–AD; Amendment 

39–16483; AD 2010–22–04] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–90–30 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires a detailed inspection 

for certain defects of the upper fasteners 

of the aft mount support fittings of the 

left and right engines, and corrective 

actions if necessary. This new AD 

requires repetitive replacement of the 

upper row of fasteners of the support 

fittings of the engine aft mount with 

new fasteners; and repetitive general 

visual inspections for defects of the 

lower row fasteners (Row B) of the 

support fittings of the left and right 

engine aft mounts, and replacement of 

all clearance fit fasteners in the lower 

row if necessary. This AD was prompted 

by reports of loose, cracked, or missing 

fasteners in the aft mount support fitting 

of the left and right engines. We are 

issuing this AD to prevent loose, 

cracked, or missing fasteners in the 

engine aft mount support fittings, which 

could lead to separation of the support 

fittings from the pylon, and could result 

in separation of the engine from the 

airplane. 

DATES: This AD is effective December 3, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 3, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800 0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; 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: 

Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5233; fax (562) 627–5210; e-mail: 

Roger.Durbin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede airworthiness 

WReier-Aviles on DSKGBLS3C1PROD with RULES

66654 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 

directive (AD) 2008–18–10, amendment 

39–15667 (73 FR 52203, September 9, 

2008). That AD applies to the specified 

products. The NPRM was published in 

the Federal Register on July 1, 2010 (75 

FR 38056). That NPRM proposed to 

require repetitive replacement of the 

upper row of fasteners (Row A) of the 

support fittings of the left and right 

engine aft mount with new fasteners. 

That NPRM also proposed to require 

repetitive general visual inspections for 

defects of the lower row fasteners (Row 

B) of the support fittings of the left and 

right engine aft mounts (that includes a 

gap check under the head or nut, and a 

torque check), as necessary for defects of 

the lower row of fasteners (Row B) of 

the support fittings of the left and right 

engine aft mounts, and replacing all 

clearance fit fasteners in the lower row 

(Row B) with new fasteners if any defect 

is found. Defects include missing, loose, 

and damaged fasteners. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 13 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Replacement ..................... 14 work-hour × $85 per 

hour = $1,190.

$152 per replacement ....... $1,342 per replacement 

cycle.

$17,446 per replacement 

cycle. 

Inspections ........................ 4 work-hours × $85 per 

hour = $340.

$0 ...................................... $340 per inspection cycle $4,420 per inspection 

cycle. 

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 have 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 

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. 

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) 

2008–18–10, Amendment 39–15667 (73 

FR 52203, September 9, 2008), and 

adding the following new AD: 

2010–22–04 McDonnell Douglas 

Corporation: Amendment 39–16483; 

Docket No. FAA–2010–0645; Directorate 

Identifier 2009–NM–200–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective December 3, 2010. 

Affected ADs 

(b) This AD supersedes AD 2008–18–10, 

Amendment 39–15667. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Corporation Model MD–90–30 airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin MD90–54A003, 

Revision 2, dated February 12, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD results from reports of loose, 

cracked, or missing fasteners in the aft mount 

support fitting of the left and right engines. 

The Federal Aviation Administration is 

issuing this AD to prevent loose, cracked, or 

missing fasteners in the engine aft support 

mount fittings, which could lead to 

separation of the support fittings from the 

pylon, and could result in separation of the 

engine from the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Replacement and Inspection 

(g) Except as required by paragraph (i) of 

this AD, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010: Replace the upper 

row of fasteners (Row A) of the support 

fittings of the left and right engine aft mounts 

with new fasteners, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. Repeat the 

replacement thereafter at intervals not to 

exceed 10,000 flight cycles. 

(h) Concurrently with any replacement 

required by paragraph (g) of this AD: Perform 

a general visual inspection for defects of the 

lower row fasteners (Row B) of the support 

fittings of the left and right engine aft 

WReier-Aviles on DSKGBLS3C1PROD with RULES

Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66655 

mounts, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. Defects include 

missing, loose, and damaged fasteners. 

(1) If no defect is found during any general 

visual inspection required by paragraph (h) 

of this AD, before further flight, insert a 

0.0015-inch feeler gauge between the washer 

and the structure, or between the fastener 

head and structure, as applicable, to detect a 

gap condition, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. A gap condition is 

a defect identified in any location where the 

feeler gauge can slip completely between a 

washer or a fastener head and the structure. 

(i) If no defect is found during any gap 

check required by paragraph (h)(1) of this 

AD, before further flight, apply torque to the 

fasteners of the lower row (Row B) to 

determine if there is a defect, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin MD90–54A003, 

Revision 2, dated February 12, 2010. A defect 

is any fastener that turns with the application 

of the specified torque. If any defect is found, 

before further flight, replace all clearance fit 

fasteners in the lower row (Row B), in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–54A003, Revision 2, dated February 

12, 2010. 

(ii) If any defect is found during any gap 

check required by paragraph (h)(1) of this 

AD, before further flight, replace all clearance 

fit fasteners in the lower row (Row B), in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–54A003, Revision 2, dated February 

12, 2010. 

(2) If any defect is found during any 

general visual inspection required by 

paragraph (h) of this AD, before further flight, 

replace all clearance fit fasteners in the lower 

row (Row B), in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–54A003, Revision 2, 

dated February 12, 2010. 

Exception to Service Bulletin Compliance 

Times 

(i) Where Boeing Alert Service Bulletin 

MD90–54A003, Revision 2, dated February 

12, 2010, specifies a compliance time after 

the original issue date on the service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Replacements and inspections 

accomplished before the effective date of this 

AD in accordance with Boeing Alert Service 

Bulletin MD90–54A003, Revision 1, dated 

November 17, 2009, are considered 

acceptable for compliance with the 

corresponding actions required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Related Information 

(l) For more information about this AD, 

contact Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; telephone 

(562) 627–5233; fax (562) 627–5210; e-mail: 

Roger.Durbin@faa.gov. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin MD90–54A003, Revision 2, dated 

February 12, 2010, to do the actions required 

by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800 0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

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

www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, 1601 Lind Avenue, 

SW., Renton, Washington. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(4) 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 October 

13, 2010. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–26555 Filed 10–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0849; Directorate 

Identifier 2010–CE–043–AD; Amendment 

39–16488; AD 2010–22–09] 

RIN 2120–AA64 

Airworthiness Directives; PILATUS 

Aircraft Ltd. Model PC–7 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

This Airworthiness Directive (AD) is 

prompted due to an occurrence when an 

aircraft had a partial in-flight separation of 

the aileron outboard bearing support. 

The aileron outboard bearing supports are 

attached with two forward attachment bolts 

and two aft attachment bolts. The forward 

attachment bolts are approximately 3.2 mm 

(0.125 inch) longer than the aft attachment 

bolts. If the aileron outboard bearing supports 

have been removed, it is possible that during 

the reinstallation of the aileron outboard 

bearing supports, the attachment bolts can be 

installed in wrong positions. Bolts that are 

installed in wrong positions can damage the 

threads in the rear attachment anchor nuts. 

Such a condition, if left uncorrected, could 

lead to in-flight separation of the aileron 

outboard bearing support, and as a 

consequence, the loss or limited 

controllability of the aircraft. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 3, 2010. 

On December 3, 2010, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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 service information identified in 

this AD, contact Pilatus Aircraft Ltd., 

WReier-Aviles on DSKGBLS3C1PROD with RULES