21528 Federal Register / Vol. 75, No. 79 / Monday, April 26, 2010 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0433; Directorate 

Identifier 2009–NM–117–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–90–30 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model MD–90–30 airplanes. This 

proposed AD would require inspecting 

for corrosion of the retract cylinder 

support fitting for the main landing gear 

(MLG) and the mating bore for the 

support fitting in the MLG trunnion 

fitting and performing corrective actions 

if necessary, and replacing cadmiumplated retract cylinder support bushings 

and bearings. This proposed AD results 

from reports of the retract cylinder 

support fitting for the MLG failing 

during gear extension and subsequently 

damaging the hydraulic system. We are 

proposing this AD to prevent corrosion 

and damage that could compromise the 

integrity of the retract cylinder support 

fitting for the MLG, which could 

adversely affect the airplane’s safe 

landing. 

DATES: We must receive comments on 

this proposed AD by June 10, 2010. 

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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0433; Directorate Identifier 

2009–NM–117–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of failure of 

the retract cylinder support fitting for 

the main landing gear (MLG) during 

gear extension, damaging the hydraulic 

system on McDonnell Douglas 

Corporation MD–80 series airplanes. 

This condition, if not corrected, could 

result in corrosion and damage that 

could compromise the integrity of the 

retract cylinder support fitting for the 

MLG, which could subsequently 

damage the hydraulic system and 

adversely affect the airplane’s ability to 

make a safe landing. 

The retract cylinder support fittings 

for the MLG on McDonnell Douglas 

Model MD–80 series airplanes have the 

same design as those installed on Model 

MD–90–30 airplanes. Therefore, Model 

MD–90–30 airplanes may be subject to 

the identified unsafe condition. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin MD90–57–016, Revision 2, 

dated April 28, 2006. The service 

bulletin describes procedures for doing 

a general visual inspection of the 

cylinder bore in the MLG support for 

corrosion, and performing corrective 

actions if necessary. 

Corrective actions include the 

following: 

• For airplanes on which a cadmiumplated fitting is installed with or 

without corrosion present: Replacing 

the cadmium-plated retract cylinder 

support fitting for the MLG with an 

electroless nickel-plated fitting, and 

replacing the cadmium-plated retract 

cylinder support bushings and bearings 

for the MLG with bushings and bearings 

having no cadmium plating in the bore. 

• For airplanes on which an 

electroless nickel-plated fitting is 

installed with no corrosion present: 

Installing the retained electroless nickelplated retract cylinder support fitting for 

the MLG, and replacing the cadmiumplated retract cylinder support bushings 

and bearings for the MLG with bushings 

and bearings having no cadmium 

plating in the bore. 

• For airplanes on which the 

electroless nickel plated fitting is 

installed with corrosion present: 

Replacing the electroless nickel-plated 

retract cylinder support fitting for the 

MLG, and replacing the cadmium-plated 

retract cylinder support bushings and 

bearings for the MLG with bushings and 

bearings having no cadmium plating in 

the bore. 

For airplanes on which an electroless 

nickel-plated fitting is installed in 

accordance with a previous issue of the 

service bulletin, no further work is 

required if the following actions have 

been accomplished. 

• An inspection for corrosion and 

damage of the cylinder bore in the MLG 

support has been performed. 

• The cadmium-plated retract 

cylinder support fitting for the MLG has 

been replaced with an electroless 

nickel-plated fitting. 

• An electroless nickel-plated retract 

cylinder support fitting for the MLG is 

already installed and has no corrosion. 

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Federal Register / Vol. 75, No. 79 / Monday, April 26, 2010 / Proposed Rules 21529 

• The cadmium-plated retract 

cylinder support bushings and bearings 

for the MLG have been replaced with 

bushings and bearings with no cadmium 

plating in the bore. 

For airplanes on which the cadmiumplated fitting is installed, and on which 

the cadmium-plated retract cylinder 

support fitting for the MLG was 

reinstalled and on which a previous 

issue of the service bulletin was 

performed, the service bulletin 

specifies: 

• Removing the cadmium-plated 

retract cylinder support fitting for the 

MLG and replacing with an electroless 

nickel-plated fitting. 

• Verifying that the cadmium-plated 

retract cylinder support bushings and 

bearings for the MLG have been 

replaced with bushings and bearings 

with no cadmium plating in the bore. 

FAA’s Determination and Requirements 

of this Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 16 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection ................................................. 1 $85 $0 $85 16 $1,360 

Replacement ............................................ 8 85 24,580 25,260 16 404,160 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), and 

3. 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

McDonnell Douglas Corporation: Docket No. 

FAA–2010–0433; Directorate Identifier 

2009–NM–117–AD. 

Comments Due Date 

(a) We must receive comments by June 10, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Corporation Model MD–90–30 airplanes, 

certificated in any category, as identified in 

Boeing Service Bulletin MD90–57–016, 

Revision 2, dated April 28, 2006. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of the 

retract cylinder support fitting for the main 

landing gear (MLG) failing during gear 

extension, and subsequently damaging the 

hydraulic system. The Federal Aviation 

Administration is issuing this AD to prevent 

corrosion and damage that could compromise 

the integrity of the retract cylinder support 

fitting for the MLG, which could adversely 

affect the airplane’s safe landing. 

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. 

Inspection and Corrective Actions 

(g) Before the accumulation of 30,000 total 

flight hours, or within 15,000 flight hours 

after the effective date of this AD, whichever 

occurs later, do a general visual inspection of 

the retract cylinder support fitting for the 

MLG and the mating bore in the MLG trunion 

fitting for corrosion, install bushings and 

bearings without cadmium plating in the 

bore, and do all applicable corrective actions, 

in accordance with Configuration 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin MD90–57–016, Revision 2, 

dated April 28, 2006. Do all applicable 

corrective actions before further flight. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

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21530 Federal Register / Vol. 75, No. 79 / Monday, April 26, 2010 / Proposed Rules 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

(h) Doing a general visual inspection, 

installing bushings and bearings, and doing 

all applicable corrective actions is also 

acceptable for compliance with the 

requirements of paragraph (g) of this AD if 

done before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

MD90–57–016, Revision 1, dated October 26, 

2005. 

(i) Doing a general visual inspection, 

installing bushings and bearings, and doing 

all applicable corrective actions is also 

acceptable for compliance with the 

requirements of paragraph (g) of this AD if 

done before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

MD90–57–016, dated September 18, 2002, 

provided that before the accumulation of 

30,000 total flight hours, or within 15,000 

flight hours after the effective date of this AD, 

whichever occurs later, electroless nickel 

fittings are installed, and bushings and 

bearings without cadmium plating in the 

bore are installed in accordance with the 

Accomplishment Instructions of any of the 

service bulletins listed in Table 1 of this AD. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION

Document Revision Date 

Boeing Service Bulletin MD90–57–016 .................................................................................................. 0 September 18, 2002. 

Boeing Service Bulletin MD90–57–016 .................................................................................................. 1 October 26, 2005. 

Boeing Service Bulletin MD90–57–016 .................................................................................................. 2 April 28, 2006. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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. Send information to ATTN: 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. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(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 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) who 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. 

Issued in Renton, Washington, on April 16, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9572 Filed 4–23–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0432; Directorate 

Identifier 2010–NM–001–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–200 and DHC–8–300 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated 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: During a recent production 

fuel system test, it was found that all 

three flapper valves located in each 

collector tank did not conform to the 

design requirements, due to the fact that 

a valve spring was installed on the 

flapper hinge pin. This valve spring 

should have been removed prior to 

installation of the valves. With the valve 

spring installed, the flapper valve is 

held closed by the valve spring, 

preventing gravity feed. In the event of 

scavenge system failure, the collector 

tank fuel level can no longer be 

maintained, potentially leading to an inflight engine shutdown. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by June 10, 2010. 

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 

W12–40, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS